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    • 专利摘要:
    It is a propulsion system (10) including a propellant (12) having a drive shaft (72), an electric machine (14) coupled to the drive shaft (72) of the impeller (12) and a motor. of combustion that has an output shaft. the propulsion system (10) additionally includes a unidirectional clutch (16) operable with at least one of the propeller drive shaft (72) and the combustion engine output shaft. the unidirectional clutch (16) allows a differential angular speed of the drive shaft (72) relative to the output shaft in a first circumferential direction and prevents a differential angular speed of the drive shaft (72) relative to the output shaft in a second circumferential direction.
    公开号:BR102017025528A2
    申请号:R102017025528-0
    申请日:2017-11-28
    公开日:2018-08-14
    发明作者:M. Vondrell Randy；Crabtree Glenn
    申请人:General Electric Company；
    IPC主号:
    专利说明:

    (54) Title: PROPULSION SYSTEM AND METHOD FOR OPERATING A PROPULSION SYSTEM (51) Int. Cl .: B64D 27/24; B64D 27/10; B64D 35/08; F16D 48/06; F02C 7/36 (30) Unionist Priority: 12/13/2016 US 15 / 377,080 (73) Holder (s): GENERAL ELECTRIC COMPANY (72) Inventor (s): RANDY M. VONDRELL; GLENN CRABTREE (85) National Phase Start Date:
    11/28/2017 (57) Abstract: It is a propulsion system (10) that includes a propeller (12) that has a drive shaft (72), an electric machine (14) coupled to the drive shaft ( 72) of the propellant (12) and a combustion engine that has an output shaft. The propulsion system (10) additionally includes a unidirectional clutch (16) operable with at least one of the drive shaft (72) of the propeller (12) and the output shaft of the combustion engine. The unidirectional clutch (16) allows a differential angular speed of the drive shaft (72) in relation to the output shaft in a first circumferential direction and prevents a differential angular speed of the drive shaft (72) in relation to the output shaft in a second circumferential direction.
    1/22 “PROPULSION SYSTEM AND METHOD FOR OPERATING A PROPULSION SYSTEM”
    Field [001] The present article refers, in general, to a hybrid electric propulsion system that uses a gas turbine engine.
    Background [002] An exemplary gas turbine engine turbine engine generally includes, in series flow order, a compressor section, a combustion section and a turbine section. During operation, ambient air is supplied to an inlet of the compressor section where one or more axial compressors progressively compress the air until it reaches the combustion section. The fuel is mixed with the compressed air and burned within the combustion section to provide combustion gases. Flue gases are routed from the combustion section to the turbine section. The flue gas flow through the turbine section drives the turbine section.
    [003] With certain propulsion systems, the turbine engine of the gas turbine engine can be used to drive, for example, a propeller. In addition, with certain propulsion systems, a secondary power supply can be used to supplement the amount of power supplied to the propeller by the gas turbine engine, or alternatively, to replace the power supplied to the propeller by the gas turbine engine. In the latter case, complications can arise if the secondary power supply additionally causes rotation of certain components of the gas turbine engine without operation of the gas turbine engine.
    [004] Consequently, a propulsion system that includes a secondary power supply with the capacity to supplement or replace the power provided by a gas turbine engine with capacity
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    2/22 to overcome the above obstacles would be particularly useful in the technique.
    Brief Description [005] Aspects and advantages of the invention will be presented in part in the description below, or they may be evident from the description, or they can be learned through the practice of the invention.
    [006] In an exemplary embodiment of the present disclosure, a propulsion system is provided. The propulsion system includes a drive shaft, an electric machine coupled to the drive shaft and a combustion engine that has an output shaft. The propulsion system additionally includes an unidirectional clutch operable with at least one between the drive shaft and the output shaft of the combustion engine. The unidirectional clutch allows a differential angular speed of the drive shaft in relation to the output shaft in a first circumferential direction and prevents a differential angular speed of the drive shaft in relation to the output shaft in a second circumferential direction.
    [007] In an exemplary aspect of the present disclosure, a method for operating a propulsion system is provided. The propulsion system includes a propeller that includes a drive shaft, an electrical machine coupled to the drive shaft, a combustion engine that has an output shaft and a unidirectional clutch operable with at least one of the drive shaft and the output shaft of the combustion engine. The method includes operating the propulsion system to feed the propellant, at least in part, with the combustion engine, so that the unidirectional clutch engages the combustion engine's output shaft to the propeller drive shaft. The method also includes operating the propulsion system to power the propellant, at least in part, with the electric machine so that the unidirectional clutch decouples the output shaft from the
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    3/22 combustion engine of the propeller drive shaft.
    [008] These and other functions, aspects and advantages of the present invention will become better understood with reference to the appended claims and the description below. The attached Figures, which are incorporated in the specification and which form part of it, illustrate the achievements of the invention and, together with the description, serve to explain the principles of the invention.
    Brief Description of the Figures [009] A complete and viable disclosure of the present invention, which includes the best mode of the same, intended for a person of common skill in the technique, is presented in the specification that refers to the attached Figures, in which:
    [010] Figure 1 is a schematic view of a propulsion system according to an exemplary embodiment of the present disclosure.
    [011] Figure 2 is a cross-sectional foreground view of a unidirectional clutch in accordance with an exemplary embodiment of the present disclosure, as can be incorporated into the exemplary propulsion system of Figure 1.
    [012] Figure 3 is a schematic view of a propulsion system according to another exemplary embodiment of the present disclosure.
    [013] Figure 4 is a schematic view of a propulsion system in accordance with yet another exemplary embodiment of the present disclosure.
    [014] Figure 5 is a schematic view of a propulsion system in accordance with yet another exemplary embodiment of the present disclosure.
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    4/22 [015] Figure 6 is a schematic view of a propulsion system in accordance with yet another exemplary embodiment of the present disclosure.
    [016] Figure 7 is a schematic view of a propulsion system in accordance with yet another exemplary embodiment of the present disclosure.
    [017] Figure 8 is a flow diagram of a method for operating a propulsion system according to an exemplary aspect of the present disclosure.
    Detailed Description [018] Reference will now be made in detail to the present embodiments of the invention, in which one or more examples of it are illustrated in the accompanying drawings. The detailed description uses numerical and letter designations to indicate features in the drawings. Similar or equal designations in the drawings and description have been used to refer to similar or equal parts of the invention. As used herein, the terms "first", "second" and "third" can be used interchangeably to distinguish components from each other and are not intended to mean a location or an importance for individual components. The terms "forward" and "rear" refer to relative positions within a gas turbine engine, with forward referring to a position close to an engine inlet and later referring to a position close to an exhaust or engine nozzle. The terms "upstream" and "downstream" refer to the relative direction in relation to the flow of fluid in a fluid passage. For example, "upstream" refers to the direction from which the fluid flows, and "downstream" refers to the direction to which the fluid flows.
    [019] Now referring to the drawings, in which the identical numerals indicate the same elements throughout all the Figures, the Figure
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    5/22 is a schematic view of a propulsion system 10 according to an exemplary embodiment of the present disclosure. For the illustrated embodiment, the propulsion system 10 generally includes a gas turbine engine (a schematic cross-sectional view of which is provided in Figure 1), a propeller 12, an electrical machine 14 and a one-way clutch 16. Each of these components, and their respective operability within the illustrated exemplary propulsion system 10, is described in more detail below.
    [020] In reference, first, to the exemplary gas turbine engine, it will be verified that the illustrated gas turbine engine is configured as a turboshaft engine, referred to in this document as “18 turboshaft engine”. However, as is discussed in more detail below, in other exemplary embodiments, the turbo-axle engine 18 can instead be configured in any other suitable manner. For example, in other exemplary embodiments, the turbo-axle engine 18 can instead be configured as a turboprop engine, a turbofan engine, or any other suitable combustion engine (such as any other suitable gas turbine engine or, for example, internal combustion engine).
    [021] As shown in Figure 1, the turbo-axis engine 18 defines an axial direction A (which extends parallel to a longitudinal center line 20 provided for reference), a radial direction R, and a circumferential direction C (that is, a direction extending over axial direction A, see Figure 2). In general, the turboshaft engine 18 includes a turbine engine 22 and an output shaft 24.
    [022] The exemplary turbine engine 22 illustrated generally includes a substantially tubular outer casing 26 that partially surrounds an annular radial inlet duct 28. The radial inlet duct 28
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    6/22 includes at least a portion that generally extends along the radial direction R, and is additionally configured to change a direction of an airflow through it, so that the resulting airflow is generally along the direction axial A. Additionally, the outer casing 26 covers, in series flow relationship, a compressor section that includes a single compressor 30; a combustion section that includes a reverse flow combustor 32; a turbine section that includes a high pressure turbine (HP) 34 and a low pressure turbine (LP) 36; and an exhaust section 38. In addition, the turbocharger engine 18 illustrated is a dual-coil engine, which includes a first coil or high-pressure (HP) shaft 40 that couples the HP 34 turbine to the compressor 30, and a low pressure (LP) coil or spindle 42 coupled to the LP 36 turbine, and which connect the LP 36 turbine in an actionable way to the output shaft 24.
    [023] The compressor section, combustion section, turbine section, and exhaust section 38 together define a flow path for turbine engine 44 through turbine engine 22. Notably, for the illustrated embodiment, the engine turbine 22 additionally includes an input guide pallet stage 46 at a front end of the turbine engine airflow path 44. Specifically, the input guide pallets 46 are positioned at least partially within the radial inlet duct 28, in which the radial inlet duct 28 is located upstream of the compressor section, which includes compressor 30. For the illustrated embodiment, the example stage of the inlet guide palettes 46 is configured as variable inlet guide palettes. However, it should be noted that, in other exemplary embodiments, entry guide palettes 46 can instead be configured as fixed entry guide palettes, and can be additionally located at any other suitable location within the duct. radial inlet 28.
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    7/22 [024] In addition, compressor 30 of the compressor section includes a plurality of compressor rotor pallet stages. More specifically, for the illustrated embodiment, the compressor 30 of the compressor section includes four stages of radially oriented rotor blades 48, and an additional stage of centrifugal compressor rotor blades 50. Additionally, between each stage of compressor rotor blades 48, 50, the compressor section includes a compressor stator pallet stage. Notably, the first stage of compressor stator palettes is configured as a stage of variable compressor stator palettes 52. In contrast, the remaining stages of compressor stator palettes are configured as fixed compressor stator palettes 56. However , it should be noted that, in other exemplary embodiments, the compressor 30 may have any other suitable configuration, which includes any other suitable number of compressor rotor pallet stages 48, 50 and any suitable number of compressor stator pallet stages. variable and / or fixed 52, 56.
    [025] As illustrated, the turbine motor 22 additionally includes a transition duct 58 immediately downstream of the compressor 30, wherein the transition duct 58 has at least one portion that generally extends along the radial direction R to provide a compressed air flow from compressor 30 to reverse flow combustion 32. Centrifugal compressor rotor pallet stage 50 is configured to assist in changing compressed air within the compressor section radially outward in transition duct 58. However Notably, in other exemplary embodiments, the combustion section cannot include the reverse flow combustion 32, and, instead, can include any suitable forward flow combustion, such as a tubular combustion, cannular combustion or annular combustion. With such an exemplary realization, the
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    8/22 compressor 30 cannot include the centrifugal compressor rotor pallet stage 50.
    [026] It will be verified that, during the operation of the turboshaft engine 18, an air volume 60 enters the turboshaft engine 18 through the radial inlet duct 28, and flows through the inlet guide palettes 46 and into the interior of the compressor 30 from the compressor section. An air pressure 60 is increased as it is routed through the compressor 30, and is then supplied to the reverse flow combustion 32 of the combustion section, where the air is mixed with fuel and burned to supply exhaust gases. combustion. The flue gases are routed through the HP 34 turbine, where a portion of thermal and / or kinetic energy from the flue gases 72 is extracted through sequential stages of the HP 62 turbine stator vanes, which are coupled to the housing. external 26, and HP 64 turbine rotor blades, which are coupled to the HP 40 rotor shaft, thus causing the HP 40 shaft to rotate, thus supporting the operation of the HP 30 compressor. The flue gases are then routed through the LP 36 turbine where a second portion of thermal and kinetic energy is extracted from the flue gases through sequential stages of LP 66 turbine stator vanes that are coupled to the outer shell 26 and LP 68 turbine rotor blades that are coupled to the LP 42 shaft, thus causing the LP 42 shaft to rotate, thereby sustaining the operation of the output shaft 24. The combustion gases are subsequently routed through the exaus section so 38 of the 22 turbine engine.
    [027] As briefly indicated, the LP 42 shaft is coupled to the LP 36 turbine, and is, in addition, mechanically coupled to the drive shaft 24. The drive shaft 24 of the turbo-axle engine 18 is operable with the various others components of the propulsion system 10.
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    9/22 [028] Still referring to Figure 1, for the illustrated embodiment, propeller 12 generally includes a propeller 70 and a drive shaft 72 configured to rotate propeller 70. More specifically, propeller 12 includes propeller 70, a propeller shaft 74, a gearbox 76 and drive shaft 72. Drive shaft 72 is configured to rotate propeller 70 through gearbox 76, and even more specifically, drive shaft 72 is configured to rotating propeller shaft 74 through gearbox 76, which in turn rotates propeller 70. However, in other exemplary embodiments, thruster 12 can be configured in any other suitable manner.
    [029] The propulsion system 10 additionally includes an electric machine 14 coupled to the drive shaft 72 of the propeller 12. Electric machine 14 generally includes a rotor 78 fixedly coupled to the drive shaft 72 and a stator 80, which is configured to remain stationary. In addition, electrical machine 14 includes an electrical line 81 to electrically connect stator 80 and / or rotor 78 of electrical machine 14 to a power source and / or a power sink. Electric machine 14 is illustrated as an inrunner electric machine 14 (i.e., an electric machine 14 with rotor 78 located radially inside stator 80). However, it should be noted that, in other embodiments, the electrical machine 14 may have any other suitable configuration. For example, in other embodiments, stator 80 may instead be located into rotor 78 along the radial direction R (that is, as an outrunner machine), or alternatively it can be configured in an axial flow configuration. . Depending on an operating condition of the propulsion system 10 and a particular configuration of the propulsion system 10, the electrical machine 14 can be configured as an electrical generator configured to draw power from the propulsion system 10 (ie, use a rotation drive shaft
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    10/22 of the thruster 12 to generate electric power) or alternatively as an electric driving machine configured to add power to the propulsion system 10 (i.e., to drive or assist in driving the drive shaft 72 of the thruster 12).
    [030] In order to effectively facilitate the various operating conditions of the electric machine 14, the exemplary propulsion system 10 of Figure 1 includes a unidirectional clutch 16 operable with at least one of the drive shaft 72 of the propeller 12 and the output shaft 24 of the gas turbine engine (ie, with drive shaft 72, with output shaft 24, or both with drive shaft 72 and output shaft 24). More particularly, for the illustrated embodiment, the unidirectional clutch 16 is operable with at least one of the drive shaft 72 of the propeller 12 and output shaft 24 of the turbo shaft motor 18 at a location between the electrical machine 14 and the turbine motor 22. The unidirectional clutch 16 allows a differential angular speed of the drive shaft 72 with respect to the output shaft 24 in a first circumferential direction C1 and prevents a differential angular speed of the drive shaft 72 with respect to the output shaft 24 in a second circumferential direction C2 (that is, a circumferential direction C opposite the first circumferential direction C1; see Figure 2).
    [031] More specifically, for the illustrated embodiment, the one-way clutch 16 is configured to decouple the drive shaft 72 from the thruster 12 from the output shaft 24 from the turboshaft engine 18 passively based on an angular speed of the output shaft 24 ( that is, a rotational speed along the circumferential direction C) generated by the turbine motor 22 in relation to an angular speed of the drive shaft 72 (i.e., a rotational speed along the circumferential direction C) generated by the electric machine 14. More specifically,
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    11/22 furthermore, for the illustrated embodiment, the one-way clutch 16 is configured to decouple the drive shaft 72 from the propeller 12 from the output shaft 24 of the gas turbine engine based on an amount of power applied to the output shaft 24 by the turbine engine 22 of the turboshaft engine 18 in relation to an amount of power applied to the drive shaft 72 by the electrical machine 14. For example, the unidirectional clutch 16 for carrying out Figure 1 is configured to disengage the drive shaft 72 of the propeller 12 of the output shaft 24 of the gas turbine engine when the power applied to the drive shaft 72 by the electrical machine 14 exceeds the power applied to the output shaft 24 by the turbine engine 22 by a predetermined limit. The predetermined limit can be based on a particular configuration of the propulsion system 10. For example, the predetermined limit can be a fixed quantity, or alternatively, it can be a ratio between the power applied to the drive shaft 72 by the electrical machine 14 and the a power applied to the output shaft 24 by the turbine engine 22. Conversely, the one-way clutch 16 is configured to couple the drive shaft 72 of the thruster 12 to the output shaft 24 of the gas turbine engine when the power applied to the shaft of the gas turbine drive 72 by electric machine 14 is less than or equal to the power applied to the output shaft 24 by the turbine motor 22 of the turboshaft motor 18.
    [032] More particularly, for the illustrated embodiment, the unidirectional clutch 16 is configured as a unidirectional mechanical clutch, passively controlled by the output shaft 24 of the turboshaft engine 18 and the drive shaft 72 of the propeller 12. For example, in certain exemplary embodiments, the one-way clutch 16 can be configured as at least one of a ratchet clutch or a cam clutch. For example, briefly referring to Figure 2, the one-way clutch 16 can be configured as a clutch
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    12/22 with ratchet. Figure 2 schematically illustrates a unidirectional clutch 16 that has such a configuration (i.e., as a ratchet clutch) since it can be incorporated into the exemplary propulsion system 10 of Figure 1. The exemplary ratchet clutch illustrated includes a plurality of ratchets 82 positioned between an inner track 84 and an outer track 86. Outer track 86 can be attached to the output shaft 24 of the turbo shaft engine 18 and the inner track 84 can be attached to the drive shaft 72 of the propeller 12 (see Figure 1) . When the inner track 84 rotates counterclockwise with respect to the outer track 86 (so that there is a positive differential angular speed of the drive shaft 72 with respect to the output shaft 24 in the first circumferential direction C1), the plurality of ratchets 82 provides substantially no resistance to such movement. For this reason, the ratchet clutch allows the positive differential angular speed between the inner track 84 / drive shaft 72 and outer track 86 / output shaft 24 and the first circumferential direction C1. Conversely, when the inner track 84 attempts to rotate clockwise with respect to the outer track 86, the plurality of turnstiles 82 rotates around each of their respective geometrical axes of rotation 88 and blocks the inner track 84 to the outer track 86 , so that no relative rotation of the inner track 84 relative to the outer track 86 in a clockwise direction is allowed. Consequently, the ratchet clutch prevents a positive differential angular speed between inner race 84 / drive shaft 72 and outer race 86 / output shaft 24 and the second circumferential direction C2.
    [033] Still referring to Figure 1, the exemplary propulsion system 10 additionally includes a brake 89 operable with the LP shaft 42. The brake 89 can engage the LP shaft 42 to retard the LP shaft 42 and disengage the clutch unidirectional 16. Brake 89 can be any brake
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    13/22 suitable 89, which includes, for example, a friction brake operable with the LP 42 axle.
    [034] However, it must be verified that, in other embodiments, any other suitable unidirectional clutch 16 can be used, and in addition, the unidirectional clutch 16 can be positioned in any other suitable location.
    [035] In addition, it should be noted that, in other exemplary embodiments, the propulsion system 10 can be configured in any other suitable way. For example, in other exemplary embodiments, the turboshaft engine can instead be configured as a reverse flow engine, so that the LP axis 42 is coupled to an output shaft 24 at a location downstream of the engine turbo-axle 10. Additionally, in still other exemplary embodiments, the propulsion system 10 cannot be an aeronautical propulsion system. For example, in other exemplary embodiments, the drive shaft 72 cannot be configured as part of the propeller 12, and can instead be used to drive any other suitable vehicle. For example, in other exemplary embodiments, the propulsion system can be a locomotive propulsion system and the drive shaft 72 can be configured as a drive shaft for turning the wheels of a wagon. Other achievements are also covered by the scope of this disclosure. For example, in still other exemplary embodiments, the propulsion system 10 can include any other suitable combustion engine (that is, in place of the turboshaft engine 18), such as any other suitable gas turbine engine, or any gas engine. adequate internal combustion.
    [036] Referring now generally to Figures 3 to 5, the operation of the propulsion system 10 according to an exemplary embodiment of the present disclosure will be described. Figures 3 to 5, each
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    14/22 one, schematically illustrate a propulsion system 10 that can be configured in substantially the same manner as the exemplary propulsion system 10 described above with reference to Figure 1. Consequently, similar or equal numbers refer to the like or equal part.
    [037] For example, the exemplary propulsion systems 10 illustrated in Figures 3 to 5 generally include a propeller 12 having a propeller 70, a gearbox 76 and a drive shaft 72; an electric machine 14 coupled to the drive shaft 72 of propeller 12 and which includes an electric line 81; a turboshaft engine 18 which includes a turbine engine 22 and a rotatable output shaft 24 with, and by, the turbine engine 22; and a one-way clutch 16 operable with at least one of the drive shaft 72 of the propeller 12 and the output shaft 24 of the turboshaft engine 18.
    [038] Referring in particular to Figure 3, the propulsion system 10 illustrated uses the electric machine 14 as an electric driving machine and additionally uses the turboshaft engine 18 as a power supply. For example, in Figure 3, the turbine engine 22 of the turboshaft engine 18 can apply a first GTE power to the output shaft 24. Similarly, electrical machine 14 (which operates as an electric drive machine) can receive electrical power from the line 81 and convert the electrical power to mechanical power, that is, a first EM power, applied to drive shaft 72 of propeller 12. The first EM power may be within a predetermined limit of the first GTE power for the realization of Figure 3. For example, the first EM power may be less than or equal to the first GTE power for the realization of Figure 3. Based on this application of power relative to the drive shaft 72, the unidirectional clutch 16 is operable for coupling the output shaft 24 of the turboshaft engine 18 to the drive shaft 72 of the propeller
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    15/22
    12, so that each of the electric machine 14 (which operates as an electric drive machine) and the turbo-axle engine 18 operate to drive the thruster 12.
    [039] Such a configuration may allow the propulsion system 10 to have access to a greater amount of power during certain higher power modes of operation that would otherwise be available by the turbo-axle engine 18 alone. For example, such a configuration may allow the propulsion system 10 to drive a propeller 12 using the turbo-axle engine 18 and electrical machine 14 (for example, as a supplementary power supply) during bypass operation modes or other modes of operation. high power operation. With such a configuration, the turboshaft engine 18 can be designed to operate more effectively during relatively low power modes, such as during driving operations, which potentially result in a more effective overall propulsion system 10.
    [040] Referring now in particular to Figure 4, the illustrated propulsion system 10 which also uses the electric machine 14 is an electric driving machine. For the realization of Figure 4, however, the turbo-axle engine 18 is not operating, or alternatively, is operating at a relatively low power level. For example, in Figure 4, the turbine engine 22 of the turboshaft engine 18 can apply a second GTE power to the output shaft 24. Similarly, electrical machine 14 (which operates as an electric driving machine) can receive electrical power from the line electrical power 81 and convert the electrical power to a mechanical power, that is, a second EM power, applied to the drive shaft 72 of the propeller 12. For the illustrated embodiment, the second EM power is not within a predetermined limit of the second GTE power. For example, the second EM power may be greater, or substantially greater than the second EM
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    16/22 GTE power to perform Figure 4. For example, the second EM power can be at least seventy-five percent (75%) greater than the second GTE power. Consequently, based on the application of power relative to the drive shaft 72, the one-way clutch 16 is operable to decouple the output shaft 24 from the turboshaft engine 18 from the drive shaft 72 of the propeller 12, so that the rotation of the drive shaft drive 72 by electric machine 14 (operating as an electric driving machine) do not pass along any torque or rotational power or torque to the output shaft 24 of the turbo-axle engine 18.
    [041] Such a configuration can allow a more efficient and sustainable hybrid electric propulsion system 10. For example, such a configuration can allow the propellant 12 to be driven substantially and completely by the electric machine 14, without turning the turbine engine 22 and the engine turbo-shaft 18. Consequently, the turbo-shaft engine 18, in such an operating mode, does not need to use power to operate various accessory systems of the turbo-shaft engine 18 (such as lubrication systems, heat exchange systems, etc.) that would otherwise be necessary if the output shaft 24 was connected to the drive shaft 72 without using the one-way clutch 16. With such a configuration, the turbo shaft motor 18 would need to be siphoned, for example, from the electric machine 14, or otherwise, operate at a minimum power level to run such accessory systems.
    [042] Referring now particularly to Figure 5, the exemplary propulsion system 10 illustrated uses electrical machine 14 as an electrical generator. For the illustrated embodiment, the turboshaft engine 18 is operating to supply power to the propulsion system 10, and more particularly, to supply power to the electrical machine 14 (which operates as an electrical generator) as well as the propeller 12. For example, the engine of
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    17/22 turbine 22 and the turboshaft engine 18 can apply a third GTE power to the output shaft 24. Since electrical machine 14 is not applying any power to the drive shaft 72, based on the application of power relative to the shaft drive 72, the unidirectional clutch 16 is operable to couple the output shaft 24 of the turboshaft engine 18 to the drive shaft 72 of the propeller 12. As illustrated, electrical machine 14 is operating to convert a portion of the mechanical power applied to the shaft drive 72 by the output shaft 24 (via the one-way clutch 16) in electrical power, that is, a third EM power. The third EM power can be released to a power sink via power line 81, while a remaining amount of the third GTE power can be used to drive the thruster 12.
    [043] Such a configuration that may allow the turbo-axle engine 18 to operate the propeller 12 of the propulsion system 10 will still be supplying electrical power to other systems within the propulsion system 10. For example, in certain exemplary embodiments, the converted electrical power by the electrical machine 14 for carrying out Figure 5 it can be used to store power within one or more energy storage devices (such as batteries). With such a configuration, energy storage devices can subsequently transfer an amount of such stored power to electrical machine 14 to substantially and completely power propellant 12 (see, for example, Figure 4), or alternatively, to increase an amount total power delivered to thruster 12 (see, for example, Figure 3).
    [044] Alternatively, in still other embodiments, the turbine engine 22 and the electric machine 14 of the propulsion system 10 of Figure 5 can be additionally used to power other propulsion devices. For example, now briefly referring to Figure 6, a
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    18/22 propulsion system 10 according to yet another exemplary embodiment of the present disclosure is provided. The exemplary propulsion system 10 of Figure 6 is illustrated operating in a substantially similar manner to the exemplary propulsion system 10 of Figure 5. However, for an embodiment of Figure 6, propellant 12 is a first propellant 12A and electrical machine 14 it is a first 14A electric machine. The exemplary propulsion system 10 of Figure 6 additionally includes a second propeller 12B and a second electric machine 14B. The second thruster 12B, similar to the first thruster 12A, includes a propeller 70B, a gearbox 76B and a drive shaft 72B. Additionally, the second electric machine 14B, similar to the first electric machine 14A, is coupled to the drive shaft 72B of the second thruster 12B and includes a rotor 78B, a stator 80B and an electric line 81B. In addition, the second electrical machine 14B is electrically coupled to the first electrical machine 14A via the respective electrical lines 81A, 81B. In such a way, the second electric machine 14B is powered by the first electric machine 14A, which allows the second electric machine 14B to drive the second thruster 12B.
    [045] Consequently, with such a configuration, the turboshaft engine 18 of the propulsion system 10 can be used to operate a plurality of thrusters 12A, 12B. For example, although the embodiment of Figure 6 includes two thrusters 12, in other exemplary embodiments, the exemplary propulsion system 10 can include any other suitable number of thrusters 12.
    [046] Additionally, it should be noted that although for each of the embodiments described above in reference to Figures 1 and 3 to 6, the propellant 12 is illustrated including a propeller 70, in other exemplary embodiments, the propellant 12 can have any other propulsion device. For example, in other exemplary embodiments, propellant 12
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    19/22 may include a fan with ducts or without ducts. In addition, although the exemplary propulsion system 10 is generally described as an aeronautical propulsion system 10 that includes a turbo-axle engine, in other exemplary embodiments, the propulsion system 10 may include any other suitable gas turbine engine (for example, turboprop, turbofan, etc.) or other combustion engine, and the propulsion system 10 can alternatively be configured as, for example, an aeroderivative propulsion system 10 for nautical or land based applications.
    [047] In addition, in other exemplary embodiments, it must be verified that the propulsion system 10 can be configured in any other suitable way. For example, now briefly referring to Figure 7, a schematic view of a propulsion system 10 is provided that can be configured in substantially the same way as the exemplary propulsion system 10 described above with reference to Figure 1. Consequently, similar numbers or equal refer to the like or equal part. More particularly, the exemplary propulsion system 10 described in Figure 7 generally includes a propeller 12 having a propeller 70, a gearbox 76 and a drive shaft 72; an electric machine 14 coupled to the drive shaft 72 of propeller 12 and which includes an electric line 81; a turboshaft engine 18 which includes a turbine engine 22 and a rotatable output shaft 24 with, and by, the turbine engine 22; and a one-way clutch 16 operable with at least one of the drive shaft 72 of the propeller 12 and the output shaft 24 of the turboshaft engine 18.
    [048] However, for an embodiment of Figure 7, the electrical machine 14 is configured in parallel with the output shaft 24 of the turbo shaft motor 18. More particularly, the electrical machine is operable with the drive shaft 72 of the propeller 12 , which is rotatable with the propeller 70 through the
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    20/22 gearbox 76. Additionally, the output shaft 24 of the turbo shaft engine 18 is rotatable with the propeller 70 through gearbox 76. Furthermore, for the illustrated embodiment, the one-way clutch 16 is operable with the shaft outlet 24 of the turboshaft engine 18. In such a way, the one-way clutch 16 of Figure 7 can operate in substantially the same way as the exemplary one-way clutches 16 described above with reference to Figures 1 to 6. Notably, in certain embodiments, the shaft outlet 24 can be formed from a plurality of distinct components.
    [049] Referring now to Figure 8, a method (200) for operating a propulsion system according to an exemplary aspect of the present disclosure is provided. The exemplary method (200) can be operable with one or more exemplary propulsion systems described above with reference to Figures 1 to 7. Consequently, the propulsion system can include a propeller that has a drive shaft, an electrical machine coupled to the shaft drive, a combustion engine that has an output shaft (or in certain exemplary aspects, a gas turbine engine that has a turbine engine and an output shaft), and a unidirectional clutch operable with at least one of the propeller drive shaft and the gas turbine engine output shaft.
    [050] As illustrated, the example method (200) generally includes (202) operating the propulsion system to power the propellant at least in part with the gas turbine engine so that the unidirectional clutch engages the output shaft of the gas turbine engine to the propeller drive shaft. More specifically, for the exemplary aspect of Figure 8, operating the propulsion system to power the propellant at least in part with the gas turbine engine at (202) includes (204) operating the electric machine as an electric generator. With such an aspect
    Petition 870170092122, of 11/28/2017, p. 77/94
    For example, the propulsion system can provide electrical power to, for example, one or more power storage devices or a separate power heatsink. In particular, for the exemplary aspect illustrated, operating the electrical machine as an electrical generator in (204) includes (206) in powering a second propellant of the propulsion system. Such an exemplary aspect can be used with, for example, the exemplary propulsion system described above with reference to Figure 6.
    [051] At a different point in time than (204) and (206), operating the propulsion system to power the propellant at least in part with the gas turbine engine at (202) additionally includes (208) operating the propulsion system to power the propellant with both the gas turbine engine and the electric machine. Consequently, operating the propulsion system at (208) includes operating the electric machine as an electric driving machine. More specifically, for the exemplary aspect of Figure 8, operating the propulsion system to power the propellant with both the gas turbine engine and the electric machine in (208) includes (210) operating the gas turbine engine in a high power mode. For example, the high power mode can be a bypass operation mode, where a maximum amount of power can be desired.
    [052] Still referring to Figure 8, at a different point in time than (202), the example method (200) additionally includes (212) operating the propulsion system to power the propellant at least in part with the electric machine , so that the one-way clutch decouples the gas turbine engine output shaft from the propeller drive shaft. Particularly, for the exemplary aspect described in Figure 8, operating the propulsion system to power the propellant at least in part with the electric machine in (212) includes in (214) operating the propulsion system to supply the propellant substantially and completely with The
    Petition 870170092122, of 11/28/2017, p. 78/94
    22/22 electric machine. Consequently, operating the propulsion system at (212) includes operating the electric machine as an electric driving machine. As will be verified, the one-way clutch transits from the output shaft coupling to the drive shaft to decouple the output shaft from the drive shaft automatically based on a torque applied to the output shaft by the gas turbine engine in relation to a torque applied to the drive shaft by the electric machine. In such a way, the unidirectional clutch can be configured as a passively controlled unidirectional clutch.
    [053] This written description uses examples to reveal the invention, including the best way, and also to allow anyone skilled in the art to practice the invention, including creating and using any devices or systems and carrying out any built-in methods. The patentable scope of the invention is defined by the claims and may include other examples that occur to those skilled in the art. Such other examples are intended to fall within the scope of the claims, if they include structural elements that do not differ from the literal language of the claims or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims.
    Petition 870170092122, of 11/28/2017, p. 79/94
    1/4
    权利要求:
    Claims (6)
    [1]
    Claims
    1. PROPULSION SYSTEM (10) characterized by the fact that it comprises:
    a drive shaft (72);
    an electric machine (14) coupled to the drive shaft (72); a combustion engine comprising an output shaft; and a one-way clutch (16) operable with at least one of the drive shaft (72) and the output shaft of the combustion engine, where the one-way clutch (16) allows a differential angular speed of the drive shaft (72) in relation to the output axis in a first circumferential direction and prevents a differential angular speed of the drive axis (72) in relation to the output axis in a second circumferential direction.
    [2]
    2. PROPULSION SYSTEM (10), according to claim 1, characterized by the fact that the combustion engine additionally comprises a turbine engine, in which the output shaft is rotatable with the turbine engine.
    [3]
    3. PROPULSION SYSTEM (10), according to claim 2, characterized by the fact that the unidirectional clutch (16) is configured to decouple the drive shaft (72) from the output shaft passively based on an angular speed of the output shaft generated by the turbine engine in relation to an angular speed of the drive shaft (72) generated by the electric machine (14).
    [4]
    4. PROPULSION SYSTEM (10), according to claim 3, characterized by the fact that the unidirectional clutch (16) is configured to decouple the drive shaft (72) from the output shaft when the power applied to the drive shaft (72) by the electric machine (14) exceeds the power applied to the output shaft by the turbine engine by a
    Petition 870170092122, of 11/28/2017, p. 80/94
    1/8
    Petition 870170092122, of 11/28/2017, p. 84/94
    2/8 fig.2
    Petition 870170092122, of 11/28/2017, p. 85/94
    3/8
    Petition 870170092122, of 11/28/2017, p. 86/94
    4/8
    Petition 870170092122, of 11/28/2017, p. 87/94
    [5]
    5/8 r ^.
    Petition 870170092122, of 11/28/2017, p. 88/94
    [6]
    6/8
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    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US3673802A|1970-06-18|1972-07-04|Gen Electric|Fan engine with counter rotating geared core booster|
    GB1309721A|1971-01-08|1973-03-14|Secr Defence|Fan|
    US4615008A|1982-12-22|1986-09-30|United Technologies Corporation|Pulse record data capture for electrostatic engine diagnostics|
    US4625280A|1982-12-28|1986-11-25|United Technologies Corporation|Sectional distress isolating electrostatic engine diagnostics|
    JPH0343499B2|1984-01-21|1991-07-02|Nsk Warner Kk|
    GB2195712B|1986-10-08|1990-08-29|Rolls Royce Plc|A turbofan gas turbine engine|
    US20080006739A1|2005-12-02|2008-01-10|Kazuhiko Mochida|Vehicle power train including at least two power sources|
    US20080184906A1|2007-02-07|2008-08-07|Kejha Joseph B|Long range hybrid electric airplane|
    US7819625B2|2007-05-07|2010-10-26|Siemens Energy, Inc.|Abradable CMC stacked laminate ring segment for a gas turbine|
    US8177474B2|2007-06-26|2012-05-15|General Electric Company|System and method for turbine engine clearance control with rub detection|
    US7916311B2|2008-10-31|2011-03-29|General Electric Company|Method and system for inspecting blade tip clearance|
    US20120083173A1|2010-10-03|2012-04-05|Mcmillan Scott|Marine Propulsion Devices, Systems and Methods|
    US20120209456A1|2011-02-15|2012-08-16|Government Of The United States, As Represented By The Secretary Of The Air Force|Parallel Hybrid-Electric Propulsion Systems for Unmanned Aircraft|
    US9322280B2|2011-08-12|2016-04-26|United Technologies Corporation|Method of measuring turbine blade tip erosion|
    WO2013082083A1|2011-11-28|2013-06-06|Icr Turbine Engine Corporation|Hybrid drive train for a gas turbine engine|
    US9063030B2|2012-02-14|2015-06-23|Computational Systems, Inc.|Apparatus and method for visualizing the position of a rotating structure with respect to a stationary structure|
    US9174741B2|2012-07-09|2015-11-03|Mcmaster University|Hybrid powertrain system|
    US9395270B2|2012-10-19|2016-07-19|Florida Power & Light Company|Method and system for monitoring rotor blades in combustion turbine engine|
    JP5571151B2|2012-11-09|2014-08-13|三菱重工業株式会社|Ship propulsion device, ship, and ship propulsion method|
    FR2998542B1|2012-11-26|2015-07-17|Eurocopter France|METHOD AND AIRCRAFT WITH ROTARY WING WITH THREE ENGINES|
    ES2500015B1|2013-02-28|2015-06-23|Axter Aerospace S.L.|Electric auxiliary power system for piston engine aircraft|
    DE102013209538B4|2013-05-23|2020-12-03|Robert Bosch Gmbh|Hybrid propulsion for power-powered aircraft, power-powered aircraft with hybrid drive and associated operating method|
    CN203372386U|2013-06-07|2014-01-01|哈尔滨耦合动力工程技术中心有限公司|Ship hybrid power system integrated by diesel engine, generator and motor|
    US9878796B2|2014-03-27|2018-01-30|United Technologies Corporation|Hybrid drive for gas turbine engine|
    DE112015003310T5|2014-07-17|2017-03-30|Japan Aerospace Exploration Agency|A motorized aircraft and method for determining the power and number of electric motors in the motorized aircraft|
    US10430038B2|2014-07-18|2019-10-01|General Electric Company|Automated data overlay in industrial monitoring systems|
    US10408133B2|2014-10-03|2019-09-10|Pratt & Whitney Canada Corp.|Accessory drive system for a gas turbine engine|
    GB201508139D0|2015-05-13|2015-06-24|Rolls Royce Plc|Aircraft propulsion system|
    GB201511033D0|2015-05-19|2015-08-05|Rolls Royce Plc|Aircraft electrical network|
    CN204726648U|2015-06-08|2015-10-28|于海|A kind of mixed power plant peculiar to vessel|
    US9789768B1|2015-07-06|2017-10-17|Wendel Clifford Meier|Full-segregated thrust hybrid propulsion for airplanes|
    CN105416549A|2015-12-01|2016-03-23|北京赛思亿电气科技有限公司|Diesel-electricity hybrid power system based on permanent magnet motor|
    US10717539B2|2016-05-05|2020-07-21|Pratt & Whitney Canada Corp.|Hybrid gas-electric turbine engine|US10378452B1|2018-02-26|2019-08-13|The Boeing Company|Hybrid turbine jet engines and methods of operating the same|
    US11053019B2|2018-04-19|2021-07-06|The Boeing Company|Hybrid propulsion engines for aircraft|
    US10981660B2|2018-04-19|2021-04-20|The Boeing Company|Hybrid propulsion engines for aircraft|
    US10968825B2|2018-04-19|2021-04-06|The Boeing Company|Flow multiplier systems for aircraft|
    EP3584168A1|2018-06-20|2019-12-25|Airbus Operations, S.L.U.|Turbomachinery for an aircraft|
    US11091272B2|2018-07-19|2021-08-17|Raytheon Technologies Corporation|Aircraft hybrid propulsion fan drive gear system DC motors and generators|
    CN110816800B|2018-08-07|2022-02-11|大连理工大学|Diesel-fuel combined power device, hydrogen fuel cell hybrid power system and fuel supply method thereof|
    US10759540B2|2018-11-08|2020-09-01|Rolls-Royce North American Technologies, Inc.|Hybrid propulsion systems|
    US11159024B2|2018-11-08|2021-10-26|Rolls-Royce North American Technologies, Inc.|Electrical architecture for hybrid propulsion|
    US11225881B2|2018-11-08|2022-01-18|Rolls-Royce North American Technologies, Inc.|Hybrid propulsion systems|
    CN109649618A|2019-01-11|2019-04-19|中国科学院沈阳自动化研究所|The empty dual-purpose propeller of integrated water|
    CA3131966A1|2019-03-01|2020-09-10|Pratt & Whitney Canada Corp.|Mechanical disconnects for parallel power lanes in hybrid electric propulsion systems|
    EP3931090A1|2019-03-01|2022-01-05|Pratt & Whitney Canada Corp.|Aircraft propulsion system having hybrid-electric powerplant and combustion powerplant|
    US20200277071A1|2019-03-01|2020-09-03|Eric Latulipe|Torque ripple control|
    US11098655B2|2019-04-10|2021-08-24|United Technologies Corporation|Variable multiple-drive gas turbine engine|
    US10907494B2|2019-04-30|2021-02-02|Rolls-Royce North American Technologies Inc.|Parallel hybrid propulsion system|
    CN110481750A|2019-08-19|2019-11-22|中国舰船研究设计中心|The ship single shaft two-shipper propulsion system of integral vibration isolation|
    EP3805107A1|2019-10-08|2021-04-14|Airbus SAS|Hybrid propulsion system for aircraft, method of operating a hybrid propulsion system, and a hybrid aircraft|
    US10941707B1|2019-10-18|2021-03-09|The Boeing Company|Hybrid turbine engines, aircraft including the same, and associated methods|
    US11203439B2|2019-10-18|2021-12-21|The Boeing Company|Rotary electric engines, aircraft including the same, and associated methods|
    US20210355869A1|2020-05-15|2021-11-18|Pratt & Whitney Canada Corp.|Reverse-flow gas turbine engine with electric motor|
    US11149803B1|2020-06-07|2021-10-19|Textron Innovations Inc.|Mechanism and method to engage/disengage a sprag clutch using actuators|
    CN112046762B|2020-09-07|2021-10-22|南京航空航天大学|Turboprop engine-based hybrid unmanned aerial vehicle and take-off and landing control method thereof|
    CN112977848B|2021-03-30|2021-10-12|上海尚实能源科技有限公司|Power system of hybrid turboprop engine|
    法律状态:
    2018-08-14| B03A| Publication of a patent application or of a certificate of addition of invention [chapter 3.1 patent gazette]|
    2022-01-25| B06W| Patent application suspended after preliminary examination (for patents with searches from other patent authorities) chapter 6.23 patent gazette]|
    优先权:
    申请号 | 申请日 | 专利标题
    US15/377,080|US10837304B2|2016-12-13|2016-12-13|Hybrid-electric drive system|
    US15/377,080|2016-12-13|
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