• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    An aircraft turbomachine, comprising at least one flow line of a flow (I) of combustion gas, characterized in that it comprises at least one peripheral member (50) internally defining a passage space (52). another gas flow, said member comprising means for circulating at least a portion of said flow of combustion gas around its entire periphery, an inner peripheral surface of Coanda, and means for ejecting said at least a portion said flue gas flow on said Coanda surface so that, in operation, said other gas flow is Coanda-driven through said gap.
    公开号:FR3036140A1
    申请号:FR1554167
    申请日:2015-05-11
    公开日:2016-11-18
    发明作者:Josselin Coupard；Benjamin James William Godard
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] TECHNICAL FIELD The present invention relates to an aircraft turbomachine in which the Coandâ effect is used. STATE OF THE ART An aircraft turbomachine conventionally comprises, from upstream to downstream, in the direction of flow of the gases, at least one compressor module intended to compress an air flow, an annular combustion chamber in which wherein the flow of compressed air is mixed with fuel then burned, and at least one turbine module in which the flow of combustion gas is expanded to drive a turbine shaft. The turbomachine generally comprises at its upstream end a blower comprising a bladed wheel intended to compress a flow of air entering the turbomachine, this air flow dividing downstream of the blower into a primary flow supplying the compressor module. and intended to produce the aforementioned flow of combustion gas, and a secondary flow intended to flow around the motor of the turbomachine and inside a nacelle. Said boat is externally swept by a tertiary air flow. This description is applicable to a type of turbomachine, here double flow (primary and secondary) and usually also double body. There are other types of turbomachine, such as for example single flow. In this case, the entire flow of air entering the turbomachine and passing through the fan feeds the engine of the turbomachine, and the flow of air flowing around the nacelle can be considered as a secondary flow. Another type of turbomachine known as a turboprop engine is also known, this type of turbomachine comprising at least one external propeller 30 without a fairing intended to replace the aforementioned fan. As in the case of the above-mentioned single-flow turbomachine, the entire primary air flow 3036140 2 entering the turbomachine feeds the engine of the turbomachine, and the secondary air flow flowing around the nacelle is accelerated and compressed by the outer propeller to generate a propulsive force.
    [0002] Current turbomachines are subject to high thermal stresses and must first ensure a propulsive function. This results in rotating parts emitting noise (blower in particular), and a significant fuel consumption. In the context of noise reduction and fuel consumption, the present invention proposes to use the Coand® effect in a turbomachine. The Coandà effect is the result of the attraction of a gas flow by a Coandà surface. The gas flow follows the surface of Coandà and undergoes a deviation before detaching it with a trajectory different from that which it had upstream. SUMMARY OF THE INVENTION The present invention proposes to use this effect to attribute to the turbomachine a complementary thrust capacity. The invention proposes for this purpose an aircraft turbomachine, comprising at least one flow vein of a flow of combustion gas, characterized in that it comprises at least one peripheral member internally delimiting a passage space. a further gas stream, said member having means for circulating at least a portion of said flue gas stream throughout its periphery, an inner peripheral surface of Coand, and means for ejecting said at least one part of said flue gas stream on said Coandà surface so that, in operation, said other gas stream is Coandà-driven through said space. The invention thus proposes to exploit the flow of combustion gas at the outlet of the turbomachine to provide a complementary thrust thanks to the Coandà effect.
    [0003] The turbomachine according to the invention can thus be considered as equipped with a blower (additional) without blades. The combustion gases are ejected on an inner peripheral surface of Coandà of the peripheral member to force and accelerate the other air flow through the space 5 delimited by the peripheral member. This other air flow then provides a complementary thrust to the turbomachine. Airlines are finding it increasingly difficult to reduce their operating costs. Improving the thermo-propulsive performance of a turbomachine is a key improvement for engine manufacturers.
    [0004] Exploiting this bladeless fan technology can then be a solution for improving the thermo-propulsive performance. Moreover, the blower being without blades, problems of ingestion or losses of fan blades are no longer necessary. In the case where the or each peripheral member is disposed on one side of the turbomachine, the flow of combustion gases could be conveyed substantially radially from the inside to the outside with respect to the longitudinal axis of the turbomachine , up to the organ or each organ that could be considered a "blower (without blades) centrifugal". The or each peripheral member may, however, be disposed anywhere with respect to the turbomachine. The turbomachine according to the invention may comprise one or more of the following characteristics, taken separately from each other or in combination with each other: the or each member forms a loop, the or each member is hollow and comprises a internal circulation cavity of said at least a portion of said flow of combustion gas, the or each member comprises at least one ejection slot which opens into said internal cavity, the or each member comprises an upstream edge of said another flow of gas and a downstream edge of leakage of said other gas flow, said leading edge 3036140 4 having in section a substantially curved shape and said trailing edge having in section a substantially pointed shape, the turbomachine comprises two peripheral members which are substantially diametrically opposed with respect to a longitudinal axis of the turbomachine, said two peripheral members are located around said axis respectively. t at 3 o'clock and 9 o'clock (with the advantage of having a suitable ground clearance), or 12 o'clock and 6 o'clock, by analogy with the dial of a clock, the turbomachine can be configured so that the whole of said gas flow combustion engine feeds said one or more members, the turbomachine can be configured so that said or each of said members is fed by at least a part of said other gas flow; preferably, a part of said flow of combustion gas called primary flow or ventilated gases in the nacelle said secondary flow, feeds said body or bodies, the remaining primary flow flowing as conventionally in a turbomachine, - said other flow of gas is or comprises a stream flowing around a nacelle of the turbomachine. DESCRIPTION OF THE FIGURES The invention will be better understood and other details, characteristics and advantages of the invention will emerge more clearly on reading the following description given by way of nonlimiting example and with reference to the appended drawings in which: - Figure 1 is a schematic axial sectional view of a turbomachine 25 double body and double flow; FIG. 2 is a schematic view of the upstream face of a double-body and double-flow turbomachine according to the invention; - Figure 3 is a schematic axial sectional view of the turbomachine of Figure 2; FIG. 4 is a schematic view of a member of the turbomachine of FIG. 2; FIG. 4a is a view on a larger scale of a detail of FIG. 4; - Figure 5 is a schematic view of a turbomachine double body and single flow according to the invention, seen from upstream; and FIG. 6 is a diagrammatic view in axial section of the turbomachine 5 of FIG. 5. DETAILED DESCRIPTION Referring firstly to FIG. 1, which schematically represents a double-body, double-flow aircraft turbine engine 10.
    [0005] The turbomachine 10 conventionally comprises a gas generator 12 on either side of which are arranged a low-pressure compressor 14 and a low-pressure turbine 16, this gas generator 12 comprising a high-pressure compressor 18, a combustion chamber 20 and a high pressure turbine 22. Thereafter, the terms "upstream" and "downstream" are considered according to a main direction F of gas flow in the turbomachine, this direction F being parallel to the longitudinal axis A of the turbomachine. The low pressure compressor 14 and the low pressure turbine 16 form a low pressure body or LP, and are connected to each other by a low pressure shaft or BP 24 centered on the axis A. Similarly, the compressor 18 and the high pressure turbine 22 form a high pressure body or HP, and are connected to each other by a high pressure shaft or HP 26 centered on the axis A and arranged around the BP shaft 24 The turbomachine 10 further comprises, at the front of the gas generator 12 and the low-pressure compressor 14, a fan 28. This fan 28 is rotatable along the axis A, and surrounded by a fan casing 30. It is driven indirectly by the LP shaft 24, for example by means of a gearbox 32 (not mandatory) arranged between the BP body and the fan 28, being disposed axially between the latter and the BP compressor 14.
    [0006] In addition, the turbomachine 10 defines a first channel 34 to be traversed by a primary flow, and a secondary channel 36 to be traversed by a secondary flow located radially outwardly relative to the primary flow. This secondary channel 36 is delimited radially outwards by a radially inner wall of a nacelle 30, this wall comprising an outer shell 38 of an intermediate casing 40. The intermediate casing 40 also comprises a hub connected to the outer shell 38 through the radial arms 42. The secondary channel 36 is delimited radially inwardly by an outer wall 10 of an annular inter-vein compartment 44, which comprises an inner wall surrounding in particular the compressor BP 14 and HP 18 The flow of air entering the turbomachine 10 is divided downstream of the fan 28 to provide the primary flow I flowing in the channel 34 and the secondary flow II flowing in the channel 36. The primary flow I will be mixed with fuel and then combusted in the combustion chamber to produce combustion gases which will be expanded in the high pressure turbine 22 and the low pressure turbine 16 before being expelled. ulsés in a nozzle 46 of the turbomachine. The secondary flow II flows around this nozzle 46. Moreover, a tertiary air flow III flows around the nacelle 30 of the turbomachine. The present invention proposes to improve the propulsion efficiency of this type of turbomachine, for example, by using the Coand® effect. FIGS. 2 and 3 show a first embodiment of the invention in which the turbomachine 10 is of the double-body and double-flow type, as previously described. Thus, the foregoing description concerning the turbomachine of FIG. 1 applies to the turbomachine 10 of FIGS. 2 and 3. The turbomachine of FIGS. 2 and 3 differs from that of FIG. in addition to at least one peripheral member 50, here at the number of two, each member 50 delimiting an internal space 52 for passage of tertiary flow III. Each member 50 comprises means for circulating a portion of the flow of combustion gas, that is to say the primary flow I over its entire periphery, an inner peripheral surface of Coandà, and means for ejection of combustion gas on the Coandà surface so that, in operation, the portion of the tertiary flow III passing into the inner space 52 is driven and accelerated by Coandà effect and provide a thrust complementary to the turbomachine.
    [0007] In the example shown, better visible in Figures 4 and 4a, each member 50 comprises a ring having an axis of revolution B. The axes of revolution B of the rings 50 of the turbomachine are substantially parallel to each other and to the axis A. Axes A and B are coplanar and are here substantially in the same substantially horizontal plane. The members 50 are substantially diametrically opposed with respect to the axis A. As can be seen in FIG. 2, the members 50 are located respectively at 3 and 9 o'clock around the axis A, by analogy with the dial of a clock . Each member 50 or ring is hollow and comprises an outer peripheral wall 20 and an inner peripheral wall 56. Each member or ring has in longitudinal section (along the axis B) an aerodynamic profile and comprises an upstream edge 58 of attack of the stream III and a trailing edge 60 of the flow III. The outer wall 54 is substantially cylindrical. The inner peripheral wall 56 is substantially frustoconical and flared from upstream to downstream, radially outward. The leading edge 58 is convexly curved or rounded in shape and the trailing edge 60 has a pointed or tapered shape. The inner peripheral surface of the inner peripheral wall 56 forms a surface of Coandà 62.
    [0008] The outer and inner walls 54, 56 define between them an internal cavity 64 for circulating the combustion gases. The inner peripheral wall 56 comprises, upstream of the Coandà surface and near the leading edge 58, an annular slot 66 for ejecting the combustion gases 5 towards the center of the ring and towards the downstream side. The slot 66 is defined upstream by an annular exhaust lip 68 and downstream by an annular dome 70 Coandà disruption. By Coandà effect, the flow of gas ejected by the slot 66 on the dome 70 will flow along the surface of Coandà and close thereto. The flow shaves the profile, follows it and produces a surface depression with accelerating virtues. This produces surrounding depressions in chains, which promote the drive and the acceleration of the tertiary flow III through the internal space 52. As seen in FIG. 2, the peripheral members 50 are connected by substantially radial arms 72. or not to the nozzle 46 or a centrifugal turbine 74, shown in Figure 3, located at the downstream end of the turbomachine. The arms 72 are hollow and comprise internal conduits for the circulation of the combustion gases from the nozzle 46 to the internal cavities 64, shown in FIG. 4a, of the peripheral members 50. The arrows of FIGS. 2 and 3 thus show the path at least a portion of the combustion gases at the outlet of the nozzle 46. These gases circulate radially from the inside to the outside so that one can consider the peripheral members 50 as forming a centrifugal blower. The gases taken from the turbomachine are conveyed by the arms 72 and divide into two parts at the radially outer ends of each arm to respectively supply two sectors of each peripheral member 50. The combustion gases circulate around the circumference of the peripheral members 50 and are ejected onto Coandà surfaces via slits 66. The flue gas flow portions are compressed at their inlets 30 into slits 66 and at their slit outlets. These constrictions create overpressures of gas flows ejected on the surfaces of Coanda. These ejections create low pressure zones at the outlet of the slots, which leads to a suction effect of the tertiary flow air III. The ejected streams mix with tertiary air flow III and are guided by Coandâ surfaces downstream. The combination of the drive and the acceleration of the tertiary flow III causes a high speed of the gases in the internal spaces 52. In operation of the turbomachine, tertiary flow air III rushes into the internal spaces. 52 of the peripheral members 50 and is accelerated by Coandà effect to provide a push complementary to the main thrust provided here by the secondary flow II. The arms 72 are preferably shaped to limit the pressure losses in the flow vein of the secondary flow II through which they pass. In another variant not shown, the gases that can be withdrawn come in part from the secondary flow II, and they constitute only a part of the flow to provide additional thrust by impacting the initial thrust to a minimum. All or part of the flue gas streams (primary flow I) can supply the organs. FIGS. 5 and 6 show another embodiment of the invention in which the turbomachine 10 is of the double-body and single-flow type. The turbomachine of FIGS. 5 and 6 differs from that of FIG. 1 essentially in that the entire flow of air entering the turbomachine, called the primary flow, enters the engine and is used to produce the flow of combustion gas. . As in the above example, the turbomachine comprises two peripheral members 50 which are similar to those described in the foregoing. Each member here defines an internal space 52 for passage of the secondary flow II which flows around the nacelle 30 of the turbomachine. The operation of this turbomachine is similar to that of the turbomachine of FIGS. 2 and 3, with the exception that the thrust provided by the peripheral members 50 may be the only thrust provided if all combustion gas feeds the organs, or a complementary thrust if the organs are fed by a portion of the flow of combustion gas, the other part of this flow providing the main thrust of the turbomachine.
    [0009] In another variant not shown of embodiment of the invention, the turbomachine could comprise a number of members 50 different from two and for example from three or four. In the case where it comprises four members, they could be regularly distributed around the axis A and be for example arranged at 3h, 6h, 9h and 12h by 10 analogy with the dial of a clock.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. An aircraft turbomachine (10) comprising at least one flow line of a flue (I) of combustion gas, characterized in that it comprises at least one peripheral member (50) internally defining a space (52) passing another flow of gas (II, III), said member comprising means for circulating at least a portion of said flow of combustion gas around its entire periphery, an inner peripheral surface of Coandà (62), and means (66) for ejecting said at least a portion of said flue gas stream onto said Coandà surface so that, in use, said other gas stream is Coand-driven through said gap.
    [0002]
    2. Turbomachine (10) according to claim 1, wherein the or each member (50) forms a loop.
    [0003]
    3. The turbomachine (10) according to claim 1 or 2, wherein the or each member (50) is hollow and comprises an internal cavity (64) for circulating said at least a portion of said flow of combustion gas.
    [0004]
    4. Turbomachine (10) according to claim 3, wherein the or each member (50) comprises at least one ejection slot (66) which opens into said internal cavity (64).
    [0005]
    5. Turbomachine (10) according to one of the preceding claims, wherein the or each member (50) comprises an upstream edge (58) of said other gas flow attack and a downstream edge (60) leakage of said other stream gas, said leading edge having in section a substantially convex shape and said trailing edge having in section a substantially pointed shape.
    [0006]
    6. Turbomachine (10) according to one of the preceding claims, comprising two peripheral members (50) which are substantially diametrically opposed with respect to a longitudinal axis (A) of the turbomachine. 3036140 12
    [0007]
    7. Turbomachine (10) according to claim 6, wherein said two peripheral members (50) are located around said axis (A) respectively at 3h and 9h, or 12h and 6h, by analogy with the dial of a clock. 5
    [0008]
    8. Turbomachine (10) according to one of the preceding claims, configured so that the entire flow of combustion gas feeds said body or bodies.
    [0009]
    9. Turbomachine (10) according to one of claims 1 to 7, configured so that said or each of said members is fed by at least a portion of said other gas flow (II, III).
    [0010]
    10. Turbomachine (10) according to one of the preceding claims, wherein said other gas stream (II, III) is or comprises a stream flowing around a nacelle (30) of the turbomachine. 15
    类似技术:
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    同族专利:
    公开号 | 公开日
    FR3036140B1|2019-11-15|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR935340A|1946-10-28|1948-06-16|Flow enhancer for reactors and compressors|
    US3711013A|1971-04-26|1973-01-16|Rohr Corp|Thrust control and sound apparatus|
    US4332529A|1975-08-11|1982-06-01|Morton Alperin|Jet diffuser ejector|
    FR2369427A1|1976-11-01|1978-05-26|Arborg O J M|PROPULSION TUBE FOR MEANS OF TRANSPORTATION IN AIR OR WATER|US10464668B2|2015-09-02|2019-11-05|Jetoptera, Inc.|Configuration for vertical take-off and landing system for aerial vehicles|
    US10875658B2|2015-09-02|2020-12-29|Jetoptera, Inc.|Ejector and airfoil configurations|
    US11001378B2|2016-08-08|2021-05-11|Jetoptera, Inc.|Configuration for vertical take-off and landing system for aerial vehicles|
    US11148801B2|2017-06-27|2021-10-19|Jetoptera, Inc.|Configuration for vertical take-off and landing system for aerial vehicles|
    法律状态:
    2016-05-25| PLFP| Fee payment|Year of fee payment: 2 |
    2016-11-18| PLSC| Search report ready|Effective date: 20161118 |
    2017-04-27| PLFP| Fee payment|Year of fee payment: 3 |
    2018-02-09| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170717 |
    2018-04-23| PLFP| Fee payment|Year of fee payment: 4 |
    2019-04-19| PLFP| Fee payment|Year of fee payment: 5 |
    2020-04-22| PLFP| Fee payment|Year of fee payment: 6 |
    2021-04-21| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1554167A|FR3036140B1|2015-05-11|2015-05-11|AIRCRAFT TURBOMACHINE WITH COANDA EFFECT|
    FR1554167|2015-05-11|FR1554167A| FR3036140B1|2015-05-11|2015-05-11|AIRCRAFT TURBOMACHINE WITH COANDA EFFECT|
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