• 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:
    A fuel injection system is planned. The system has a fuel supply arm (34) which, in use, extends inward from an outer casing (30) of the combustion equipment (15) of a turbine engine gas (10) to a flame tube (32) of the combustion equipment (15). The supply arm (34) terminates in an injection nozzle (40) that enters a flame tube head (32) to dispense fuel into the tube (32). The system further has a swirl generator (42) which, in use, is arranged coaxially with the injection nozzle (40) at the flame tube head (32). The swirl generator (42) has one or more air swirl circuits that produce respective flows of air swirling around the fuel dispensed by the injection nozzle (40). The system further has a sealing ring (46) which seals the injection nozzle (40) to the swirl generator (42), the injection nozzle (40) being detachably inserted into the sealing ring. (46) for sealing engagement therewith. The seal ring (46) has a flange portion (52), and the swirl generator (42) has a pair of retaining grooves spaced apart at a front face thereof. Opposite edges of the flange portion (52) are slidably disposed in the grooves so that the flange portion (52) engages sealingly with the front face. The swirl generator (42) has a spring mechanism (54) that holds the flange portion (52) in the grooves.
    公开号:FR3034844A1
    申请号:FR1652321
    申请日:2016-03-18
    公开日:2016-10-14
    发明作者:Alan Geary；Keith Bell
    申请人:Rolls Royce PLC；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION The present invention relates to a fuel injection system, for example for a combustion equipment of a gas turbine engine. BACKGROUND OF THE INVENTION Air jet fuel injectors are commonly used in gas turbine engines. These injectors use compressor discharge air to create a finely atomized fuel jet. The fuel nozzle of the injector typically has two or three air swirl circuits: an indoor circuit, an external circuit, and a dome circuit. An annular fuel passage between the indoor and outdoor air circuits supplies air to a pre-forming film lip. This forms a sheet of fuel that breaks down into ligaments, which are then fractionated into droplets in shear layers of the highly swirling air surrounding.
    [0002] Figure 1 shows schematically a conventional combustion equipment of a gas turbine engine. The annular combustion equipment 100 includes outer and inner air casings 102, a flame tube 106 and a plurality of circumferentially distributed air jet fuel nozzles 108.
    [0003] Each fuel injector has a feed arm 110 which extends inwardly from an integral mounting flange 112 attached to the inner surface of a boss 114 formed in the outer casing. The feed arm terminates in an injection nozzle 116 which enters a flame tube head 106. The nozzle has a fuel passage (s) and air swirl circuits. To provide an airtight seal at the point of entry of the injection nozzle 116 into the flame tube 106, the outer diameter of the nozzle is snugly fitted into a sealing ring 118, called "miniflare". Each miniflare is attached to the flame tube in such a manner that it can move tangentially and radially with respect to the combustion chamber to accommodate differential thermal tolerances and increases. If the supply arm 110 has been mounted outside the outer casing 102, it would be necessary to receive the nozzle 116 through the housing. This would require a larger boss 114 to accommodate an opening that could accommodate the passage of the nozzle, and thus would impose excess weight. The mounting of the supply arm 110 within the outer housing 102 helps to avoid the excess weight of a larger boss, but at the cost of more complex machining at the mounting flange interface. casing. In addition, it prevents the replacement of a defective fuel injector without major disassembly of the engine. SUMMARY OF THE INVENTION An object of the present invention is to provide an improved fuel injection system. A first aspect of the present invention provides a fuel injection system having: a fuel supply arm which, in use, extends inward from an outer casing of the combustion equipment from a gas turbine engine to a flame tube of the combustion equipment, the supply arm terminating in an injection nozzle which enters a flame tube head to dispense fuel into the tube; A swirl generator which, in use, is arranged coaxially with the injection nozzle at the flame tube head, the swirl generator having one or more air swirl circuit (s) which produce respective flows of air swirling around the fuel dispensed by the injection nozzle; and a sealing ring which seals the injection nozzle to the swirl generator, the injection nozzle being detachably inserted into the sealing ring for sealing engagement therewith; wherein the seal ring has a flange portion, and the swirl generator has a pair of spaced apart retention grooves at a front face thereof, opposite edges of the flange portion 3034844 being sliding in the grooves so that the flange portion engages sealingly with the front face; and wherein the swirl generator has a spring mechanism that holds the flange portion in the grooves.
    [0004] Since the injection nozzle is releasably inserted into the sealing ring, it can be easily removed from the flame tube, leaving the swirl generator in position at the flame tube head, and the sealing ring. sealing retained by the retaining grooves. The diameter of the injection nozzle can thus be reduced compared to that of the conventional fuel injector described above in connection with FIG. 1. This allows the supply arm to be mounted outside the fuel injector nozzle. outer casing, avoiding the excess weight of a large boss on the outer casing. The external assembly in turn facilitates the replacement of the defective injectors. A second aspect of the present invention provides combustion equipment for a gas turbine engine, the equipment having: an outer casing; a flame tube inside the outer casing; and one or more fuel injection systems (s) according to the first aspect.
    [0005] A third aspect of the present invention provides a gas turbine engine having the combustion equipment of the second aspect. Optional features of the invention will now be presented. These are applicable alone or in any combination with any aspect of the invention.
    [0006] The flange portion may be at the downstream end of the seal ring. With such an arrangement, the sealing ring does not need to pass through the swirl generator. Conveniently, the injection nozzle can be releasably inserted into the seal ring by a proper adjustment operation.
    [0007] The injection nozzle may have an outer surface whose diameter increases for sealing engagement with the seal ring. Such an increase in diameter can improve the contact with the sealing ring and thus improve the sealing engagement. It can also mitigate the negative effects caused by misalignment of the injection nozzle pins and the seal ring. The outer surface may be provided, for example, by a circumferential bulge. Such a bulge may have an outer surface to form a spherical interface with the seal ring. Conveniently, the grooves can be substantially aligned with the radial direction of the motor so that the seal ring can be slid radially inward to adjust the seal ring to the swirl generator and slide radially to the outside to remove the seal ring from the swirl generator. The swirl generator may have a bore through which the injection nozzle passes, the sealing ring being aligned with the bore.
    [0008] The bore may permit relative radial displacement between the injection nozzle and the swirl generator. For example, the bore may be racetrack-shaped, with the long axis of the racetrack aligned radially. The grooves may be formed by respective flanged rails at the front of the swirl generator. The spring mechanism may comprise a cantilevered spring which is shaped so that it is initially biased outwardly by the seal ring as the flange portion slides along the grooves, and so that it subsequently returns inward to retain the flange portion in the grooves as the flange portion slides further along the grooves. For example, when the grooves are formed by respective flanged rails, one of the flanged rails can conveniently provide the cantilevered spring. The opposite edges of the flange portion may be formed as flats that cooperate with the grooves to prevent rotation of the seal ring. The upstream end of the seal ring can be flared to provide an inlet area for insertion of the injection nozzle. The swirl generator may be formed integrally with the flame tube head. The swirl generator can be formed by additive manufacturing, in particular by direct laser deposition. The fuel supply arm may have a integral mounting flange at the end opposite the injection nozzle, the mounting flange being configured to be attached to an outer surface of the outer casing of the combustion equipment. .
    [0009] BRIEF DESCRIPTION OF THE DRAWINGS Embodiments of the invention will now be described by way of example with reference to the accompanying drawings, in which: Figure 1 shows schematically conventional combustion equipment of a conventional turbine engine. gas Figure 2 shows a longitudinal section through a ducted fan gas turbine engine; Figure 3 schematically shows combustion equipment of the gas turbine engine of Figure 2; Figure 4 shows more detailed views of a fuel injector nozzle and a swirl generator of the combustion equipment of Figure 3 (a) on a tangential section, and (b) on a section 15. radial; and Figure 5 shows a view of the front face of the swirl generator. Detailed Description and Other Optional Features of the Invention Referring to Figure 2, a ducted fan gas turbine engine according to the invention is generally indicated by 10 and has a main axis of rotation X-X. The engine comprises, in series of axial flow, an air inlet 11, a propulsion blower 12, an intermediate pressure compressor 13, a high pressure compressor 14, a combustion equipment 15, a high pressure turbine 16, intermediate pressure turbine 17, a low pressure turbine 18 and a base engine ejection nozzle 19. A nacelle 21 generally surrounds the engine 10 and defines the inlet 11, a bypass duct 22 and a discharge nozzle 22. 23. During operation, the air entering the inlet 11 is accelerated by the blower 12 to produce two air flows: a first air flow A in the compressor intermediate pressure 13 and a second air flow B which passes through the bypass duct 22 to provide a propulsive thrust. The intermediate pressure compressor 13 compresses the flow of air A directed therethrough before distributing this air to the high pressure compressor 14 where further compression takes place. The compressed air discharged from the high pressure compressor 14 is directed into the combustion equipment 15 where it is mixed with the fuel and the mixture is burned. The resulting hot combustion products subsequently expand through the high pressure, intermediate pressure, and low pressure turbines 16, 17, 18 and thereby entrain them before being discharged through the nozzle 19 to provide additional propulsive thrust. The high pressure, intermediate pressure and low pressure turbines respectively drive the high pressure and intermediate pressure compressors 14, 13 and the blower 12 via suitable interconnecting shafts. Figure 3 schematically shows the combustion equipment 15 of the gas turbine engine 10 of Figure 2, the equipment being equipped with a plurality of circumferentially distributed fuel injection systems of the present invention. The annular combustion equipment 15 has outer and inner housings 30 and a flame tube 32. Each fuel injection system has an injector including a fuel supply arm 34 and an injection nozzle 40 at the fuel injection level. an inner end of the supply arm. The supply arm 34 extends inwardly from an integral mounting flange 36 attached to the outer surface of a boss 38 formed in the outer casing, and the nozzle 40 enters the head of the tube. flame. In use, the fuel flows through the feed arm to be dispensed into the flame tube through the nozzle.
    [0010] A swirl generator 42 surrounds the nozzle 40 and provides one or more coaxial air swirl circuit (s). Swirling air flows from these circuits atomize the fuel dispensed through the nozzle. Conveniently, the swirl generator 42 may be integral with the head of the flame tube 32.
    [0011] Figure 4 shows more detailed views of the nozzle 40 and the swirl generator 42 (a) on a tangential section and (b) on a radial section, and Figure 5 shows a view of the front face of the swirl generator. The swirl generator 42 has a central bore 44 through which the nozzle 40 passes into the head of the flame tube 32. The bore is racetrack shaped, with the long axis of the racetrack aligned radially, 3034844 7 to allow relative radial displacement between the swirl generator and the nozzle. A floating sealing ring 46 seals the nozzle to the swirl generator 42. The swirl generator front face 48 is flat, with the exception of two flanged rails 50 which are oriented substantially parallel to the radial direction. The sealing ring 46 has a flange 52 at its downstream end, opposite edges of the flange are slidably disposed in respective grooves formed by the flanged rails 50. Thus, the sealing ring 46 can be slid radially inwardly 10 to adjust the ring to the swirl generator, and slid radially outward to remove the ring from the swirl generator. The edges of the flange 52 received in the grooves are formed as flats which cooperate with the rails to provide an anti-rotation function. The rails 50 are profiled to retain the seal ring 46 and to accommodate relative tolerances and relative thermal motions in the radial direction. The flat front face 48 of the swirl generator and the adjacent flat face of the flange 52 of the sealing ring 46 form a seal, which is forced to come into mutual contact by the pressure drop across the tube. flame 32 during engine operation. This avoids the need for a separate sealing device. The flange of one of the rails 50 is slotted to provide a cantilevered spring 54 which holds the flange 52 in the grooves. The bottom radius of the slot is sized to prevent it from acting as a site for crack initiation. The spring 54 has inlet 56 and outlet 58 chamfers to facilitate adjustment and removal of the seal ring. More particularly, the sealing ring 46 is adjusted by placing its flange 52 under the rails 50. The thrust of the sealing ring radially inwards causes contact with the inlet chamfer 56 of the spring. This action bends the spring (left in Figure 5), allowing the seal ring to pass and rest approximately centrally on the face of the swirl generator, the spring returning to its uninflected form to retain the watertight ring. The removal of the seal is the reverse of this procedure, with the seal ring pushed radially outward to contact the "outlet" bevel 58 of the spring.
    [0012] The nozzle 40 is sealingly engaged with the sealing band 46 by proper fitting of the nozzle through the center of the ring. To facilitate this procedure, the upstream end of the seal ring is flared to provide an inlet area for the nozzle and help ensure alignment of the nozzle 40 and the swirl generator 42 during installation. The nozzle may have a circumferential bulge 60 on its outer surface to improve contact with the seal ring and thus improve the seal. In particular, the bulge may provide a spherical interface with the bore 44 of the sealing ring 46, which mitigates undesirable effects, such as jamming, which may be caused by misalignment of the axes of the bore and jet.
    [0013] The retaining function provided by the flanged rails 50 is only necessary during the installation and removal of the motor or module, the sealing ring 46 being retained by the supply arm 34 and the nozzle 40 after assembly. However, advantageously, since the nozzle can be easily removed from the seal ring by reversing the correct adjustment operation, it can easily be removed from the flame tube 32, leaving the swirl generator 42 in position at the the head of the flame tube, and the sealing ring retained by the flanged rails 50. The diameter of the nozzle can be reduced compared to a nozzle that has a swirl generator integral. This in turn facilitates the replacement of the defective injectors by allowing external mounting of the supply arm 34 to the outer case 30. In particular, the boss 38 on the outer case 30 does not need to be oversized in order to 'accommodate a large opening, and therefore does not impose a great excess of weight. The swirl generator 42 has a relatively complex geometry due to the presence of vanes in its air swirl circuits. Conveniently, it can be formed by additive manufacturing, including direct laser deposition, for example, by being constructed from the front face 48. Although the invention has been described in connection with exemplary embodiments As described above, many modifications and variations will be apparent to those skilled in the art upon reading this disclosure. Therefore, the exemplary embodiments of the invention set out above are considered illustrative and not limiting. Various modifications may be made to the described embodiments without departing from the spirit and scope of the invention.
    权利要求:
    Claims (14)
    [0001]
    REVENDICATIONS1. A fuel injection system having: a fuel supply arm (34) which, in use, extends inwardly from an outer casing (30) of the combustion equipment of an engine gas turbine engine to a flame tube (32) of the combustion equipment, the fuel supply arm (34) terminating in an injection nozzle (40) which enters a head of the fuel tube flame for dispensing fuel into the tube; a swirl generator (42) which, in use, is arranged coaxially with the injection nozzle (40) at the flame tube head, the swirl generator (42) having one or more circuits (s); ) swirling air which produces respective flows of air swirling around the fuel dispensed by the injection nozzle (40); and a sealing ring (46) which seals the injection nozzle (40) to the swirl generator (42), the injection nozzle (40) being detachably inserted into the sealing ring (42) for a tight engagement with it; wherein the sealing ring (46) has a flange portion (52), and the swirl generator (42) has a pair of spaced apart retention grooves at a front face thereof, edges opposed portions of the flange portion (52) are slidably disposed in the grooves so that the flange portion (52) seals with the front face; and wherein the swirl generator (42) has a spring mechanism (54) which holds the flange portion (52) in the grooves.
    [0002]
    The fuel injection system of claim 1, wherein the flange portion (52) is at the downstream end of the seal ring (46).
    [0003]
    The fuel injection system according to claim 1 or 2, wherein the injection nozzle (40) has an outer surface (60) whose diameter increases for sealing engagement with the sealing ring (46). .
    [0004]
    A fuel injection system according to any one of the preceding claims, wherein the grooves are substantially aligned with the radial direction of the engine, so that the sealing ring (46) can be slid radially towards the interior for adjusting the sealing ring (46) to the swirl generator (42) and radially sliding outwardly to remove the sealing ring (46) from the swirl generator (42).
    [0005]
    A fuel injection system according to any one of the preceding claims, wherein the grooves are formed by respective flanged rails (50) at the front of the swirl generator (42).
    [0006]
    A fuel injection system according to any one of the preceding claims, wherein the spring mechanism (54) comprises a cantilevered spring which is shaped so that it is initially biased towards externally through the seal ring (46) as the flange portion (52) slides along the grooves, and subsequently returns inwardly to retain the flange portion (52). ) in the grooves when the flange portion (52) slides further along the grooves.
    [0007]
    A fuel injection system according to claim 6 dependent on claim 5, wherein one of the flanged rails (50) provides the cantilevered spring (54).
    [0008]
    A fuel injection system according to any one of the preceding claims, wherein the opposite edges of the flange portion (52) are formed as flats which cooperate with the grooves to prevent rotation of the sealing ring. (46).
    [0009]
    A fuel injection system according to any one of the preceding claims, wherein the upstream end of the seal ring (46) is flared to provide an inlet area for insertion of the injection nozzle. (40).
    [0010]
    The fuel injection system according to any one of the preceding claims, wherein the swirl generator (42) is formed integrally with the flame tube head (32).
    [0011]
    The fuel injection system according to any of the preceding claims, wherein the swirl generator (42) is formed by additive manufacturing.
    [0012]
    The fuel injection system according to any of the preceding claims, wherein the fuel supply arm (34) has an integral mounting flange (36) at the end opposite the injection nozzle. (40), the mounting flange (36) being configured to be attached to an outer surface of the outer casing (30) of the combustion equipment (15). 3034844 11
    [0013]
    13. Combustion equipment of a gas turbine engine, the equipment having an outer case (30); a flame tube (32) inside the outer casing (30); and one or more fuel injection systems according to any one of the preceding claims.
    [0014]
    14. A gas turbine engine having the combustion equipment of claim 13.
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    同族专利:
    公开号 | 公开日
    US20160298848A1|2016-10-13|
    US10190776B2|2019-01-29|
    GB2538146B|2019-12-04|
    FR3034844B1|2019-11-29|
    GB201506017D0|2015-05-27|
    GB201604528D0|2016-05-04|
    GB2538146A|2016-11-09|
    引用文献:
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    法律状态:
    2017-03-27| PLFP| Fee payment|Year of fee payment: 2 |
    2017-06-16| CA| Change of address|Effective date: 20170517 |
    2018-02-23| PLSC| Search report ready|Effective date: 20180223 |
    2018-03-26| PLFP| Fee payment|Year of fee payment: 3 |
    2019-03-25| PLFP| Fee payment|Year of fee payment: 4 |
    2020-03-25| PLFP| Fee payment|Year of fee payment: 5 |
    2021-03-26| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    GBGB1506017.1A|GB201506017D0|2015-04-09|2015-04-09|Fuel injector system|
    GB1506017.1|2015-04-09|
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