COMBUSTION CHAMBER ASSEMBLY

Abstract

A combustion chamber assembly comprises an annular combustion chamber casing, a combustion chamber, a fuel injector and a tubular seal. The combustion chamber comprises an upstream end wall having an aperture extending there-through. A fuel injector head of the fuel injector is locatable in the aperture in the end wall and the fuel injector head has an axis. The tubular seal is positioned between the fuel injector head and the aperture in the end wall and the tubular seal has a flange and an aperture extends there-through. The tubular seal is movable radially and circumferentially with respect to the axis of the casing. The fuel injector head is locatable in the tubular seal. The aperture in the upstream end wall has a major radial dimension and a minor circumferential dimension relative to the axis of the casing to allow insertion or removal of a lean burn fuel injector head.

Claims

1. A combustion chamber assembly comprising an annular combustion chamber casing, at least one combustion chamber, at least one fuel injector and at least one tubular seal, the combustion chamber casing having an axis and at least one aperture extending there-through, the combustion chamber having a centre line, the combustion chamber comprising an upstream end wall having at least one aperture extending there-through, the at least one fuel injector comprising a fuel feed arm, a flange and a fuel injector head, the at least one fuel injector being locatable in the at least one aperture in the annular combustion chamber casing, the flange of the at least one fuel injector being securable to the annular combustion chamber casing, the fuel injector head of the at least one fuel injector being locatable in the at least one aperture in the upstream end wall, the fuel injector head having an axis and a plurality of annular passages, the at least one tubular seal being positionable between the fuel injector head and the at least one aperture in the upstream end wall, the at least one tubular seal having a flange, an aperture extending through the at least one tubular seal, the at least one tubular seal being movable radially and circumferentially with respect to the axis of the annular combustion chamber casing, the fuel injector head being locatable in the at least one tubular seal, and the at least one aperture in the upstream end wall being oval in cross-sectional shape, the at least one aperture in the upstream end wall having a major dimension in a radial direction and a minor dimension in a circumferential direction relative to the axis of the annular combustion chamber casing and the major dimension being greater than the minor dimension.

2. A combustion chamber assembly as claimed in claim 1 wherein the centre line of the combustion chamber being arranged at an angle to the axis of the annular combustion chamber casing.

3. A combustion chamber assembly as claimed in claim 1 wherein the axis of the fuel injector head being arranged at an angle to the axis of the annular combustion chamber casing and/or at an angle to the flange of the fuel injector and parallel to the centre line of the at least one combustion chamber.

4. A combustion chamber assembly as claimed in claim 1 wherein the fuel injector head having a part spherical surface and the part spherical surface of the fuel injector head abutting the at least one tubular seal.

5. A combustion chamber assembly as claimed in claim 1 wherein the axis of the aperture through the at least one tubular seal being arranged parallel to the axis of the fuel injector head.

6. A combustion chamber assembly as claimed in claim 1 wherein the at least one aperture in the upstream end wall having an oval race track cross-sectional shape.

7. A combustion chamber assembly as claimed in claim 1 wherein the at least one aperture having a corresponding locating ring and the locating ring having an oval aperture extending there-through.

8. A combustion chamber assembly as claimed in claim 7 wherein the oval aperture in the locating ring being race track shaped.

9. A combustion chamber assembly as claimed in claim 7 wherein the locating ring being aligned with the at least one aperture in the upstream end wall.

10. A combustion chamber assembly as claimed in claim 7 wherein the locating ring being positioned axially between the flange of the tubular seal and an upstream surface of the upstream end wall.

11. A combustion chamber assembly as claimed in claim 7 wherein the locating ring being positioned within the at least one aperture in the upstream end wall.

12. A combustion chamber assembly as claimed in claim 1 wherein the at least one combustion chamber having at least one heat shield, the at least one heat shield having an oval aperture extending there-through, the aperture in the at least one heat shield being aligned with the at least one aperture in the upstream end wall.

13. A combustion chamber assembly as claimed in claim 12 wherein the oval aperture in the at least one heat shield being race track shaped.

14. A combustion chamber assembly as claimed in claim 1 comprising a locating ring having an oval shaped aperture and an oval shaped outer surface, the locating ring aligning with the oval shaped aperture in the upstream end wall and a heat shield having an oval shaped aperture aligned with the aperture in the upstream end wall.

15. A combustion chamber assembly as claimed in claim 1 wherein the at least one combustion chamber being an annular combustion chamber, the upstream end wall having a plurality of circumferentially spaced apertures extending there-through, each aperture in the upstream end wall being oval in cross-sectional shape, each aperture in the upstream end wall having a major dimension in a radial direction and a minor dimension in a circumferential direction relative to the axis of the annular combustion chamber casing and the major dimension of each aperture being greater than the minor dimension of the respective aperture.

16. A combustion chamber assembly as claimed in claim 1 wherein the at least one tubular seal having a guide feature and the combustion chamber assembly having a corresponding guide feature such that the at least one tubular seal is movable radially with respect to the axis of the annular combustion chamber casing.

17. A combustion chamber assembly as claimed in claim 1 wherein the fuel injector head having a cylindrical surface and the cylindrical surface of the fuel injector head abutting the at least one tubular seal.

18. A combustion chamber assembly comprising an annular combustion chamber casing, an annular combustion chamber, at least one fuel injector and at least one tubular seal, the combustion chamber casing having an axis and at least one aperture extending there-through, the combustion chamber having a centre line, the combustion chamber comprising a radially inner annular wall, a radially outer annular wall and an upstream end wall, the upstream end wall having at least one aperture extending there-through, the at least one fuel injector comprising a fuel feed arm, a flange and a fuel injector head, the at least one fuel injector being locatable in the at least one aperture in the annular combustion chamber casing, the flange of the at least one fuel injector being securable to the annular combustion chamber casing, the fuel injector head of the at least one fuel injector being locatable in the at least one aperture in the upstream end wall, the fuel injector head having an axis and a plurality of annular passages, the at least one tubular seal being positionable between the fuel injector head and the at least one aperture in the upstream end wall, the at least one tubular seal having a flange, an aperture extending through the at least one tubular seal, the at least one tubular seal being movable radially and circumferentially with respect to the axis of the annular combustion chamber casing, the fuel injector head being locatable in the at least one tubular seal, the fuel injector head having a part spherical surface, the part spherical surface of the fuel injector head abutting the at least one tubular seal, and the at least one aperture in the upstream end wall being oval in cross-sectional shape, the at least one aperture in the upstream end wall having a major dimension in a radial direction and a minor dimension in a circumferential direction relative to the axis of the annular combustion chamber casing and the major dimension being greater than the minor dimension.

Description

[0020] Embodiments of the invention will now be described by way of example only, with reference to the Figures, in which:

[0021] FIG. 1 is a sectional side view of a turbofan gas turbine engine.

[0022] FIG. 2 is an enlarged schematic cross-sectional view of the combustion chamber assembly shown in FIG. 1.

[0023] FIG. 3 is a further enlarged cross-sectional view of the upstream end of the combustion chamber assembly shown in FIG. 2.

[0024] FIG. 4 is a view in the direction of arrow C in FIG. 3

[0025] FIG. 5 is a cross-sectional view in the direction of arrow D in FIG. 3.

[0026] FIG. 6 is an enlarged cross-sectional view of a fuel injector head of a fuel injector shown in FIG. 2.

[0027] FIG. 7 is an alternative enlarged schematic cross-sectional view of the combustion chamber assembly shown in FIG. 1.

[0028] FIG. 8 is an enlarged alternative schematic cross-sectional view of an alternative upstream end wall of the combustion chamber assembly shown in FIG. 2 or FIG. 7.

[0029] FIG. 9 is an enlarged alternative schematic cross-sectional view of another alternative upstream end wall the combustion chamber assembly shown in FIG. 2 or FIG. 7.

[0030] FIG. 10 is an enlarged alternative schematic cross-sectional view of a further alternative upstream end wall the combustion chamber assembly shown in FIG. 2 or FIG. 7.

[0031] With reference to FIG. 1, a turbofan gas turbine engine is generally indicated at 10, having a principal and rotational axis X. The engine 10 comprises, in axial flow series, an air intake 11, a propulsive fan 12, an intermediate pressure compressor 13, a high-pressure compressor 14, combustion equipment 15, a high-pressure turbine 16, an intermediate pressure turbine 17, a low-pressure turbine 18 and an exhaust nozzle 19. A nacelle 21 generally surrounds the engine 10 and defines the intake 11, a bypass duct 22 and a bypass exhaust nozzle 23.

[0032] The gas turbine engine 10 works in the conventional manner so that air entering the intake 11 is compressed by the fan 12 to produce two air flows: a first air flow A into the intermediate pressure compressor 13 and a second air flow B which passes through the bypass duct 22 and the bypass exhaust nozzle 23 to provide propulsive thrust. The intermediate pressure compressor 13 compresses the air flow directed into it before delivering that air to the high pressure compressor 14 where further compression takes place. The compressed air exhausted from the high-pressure compressor 14 is directed into the combustion equipment 15 where it is mixed with fuel and the mixture combusted. The resultant hot combustion products then expand through, and thereby drive the high, intermediate and low-pressure turbines 16, 17, 18 before being exhausted through the nozzle 19 to provide additional propulsive thrust. The high 16, intermediate 17 and low 18 pressure turbines drive respectively the high pressure compressor 14, intermediate pressure compressor 13 and fan 12, each by suitable interconnecting shaft 24, 25 and 26 respectively.

[0033] The combustion chamber assembly 15 is shown more clearly in FIGS. 2 to 6 and the combustion chamber assembly 15 comprises an annular combustion chamber casing 30, an annular combustion chamber 32, a plurality of fuel injectors 34 and a plurality of tubular seals 36.

[0034] The annular combustion chamber casing 30 has an axis which is coaxial with the rotational axis X of the gas turbine engine 10 and the annular combustion chamber casing 30 has a plurality of apertures 38 extending there-through. The apertures 38 extend radially through the annular combustion chamber casing 30 and the apertures 38 are circumferentially spaced apart and are arranged in a common plane perpendicular to the axis of the annular combustion chamber casing 30. The apertures 38 are generally equally spaced circumferentially around the annular combustion chamber casing 30.

[0035] The annular combustion chamber 32 comprises an upstream end wall 40, a radially inner annular wall 42 and a radially outer annular wall 44. The upstream end of the radially inner annular wall 42 is secured to the upstream end wall 40 and the upstream end of the radially outer annular wall 44 is secured to the upstream end wall 40. The upstream end wall 40 is also known as a metering panel or metering wall. The upstream end wall 40 has a plurality of apertures 46 extending there-through. The apertures 46 extend perpendicularly through the upstream end wall 40 of the annular combustion chamber 32 and the apertures 46 are circumferentially spaced apart. The apertures 46 are generally equally spaced circumferentially around the upstream end wall 40 of the annular combustion chamber casing 32. The annular combustion chamber 32 and the centre line 48 of the combustion chamber 32 are arranged parallel to the axis of the annular combustion chamber casing 30 and the axis X of the turbofan gas turbine engine 10.

[0036] The annular combustion chamber 32 also comprises a plurality of heat shields 50 on the upstream end wall 40 within the annular combustion chamber 32 to protect the upstream end wall 40 from the hot combustion gases, as seen more clearly in FIG. 3. The heat shields 50 are circumferentially arranged side by side on the upstream end wall 40 and each heat shield 50 has a central aperture 52 extending there-through which is aligned with, e.g. arranged generally coaxially with, a respective one of the apertures 46 in the upstream end wall 40. The heat shields 50 are adjacent to and spaced from the upstream end wall 40 of the annular combustion chamber 32. Each heat shield 50 is secured to the upstream end wall 40 by a plurality of threaded studs 57 which extend from the heat shield 50 through apertures in the upstream end wall 40 and which thread into corresponding nuts 59. However, the heat shields 50 may be secured to the upstream end wall 40 by other suitable arrangements. Each heat shield 50 has peripheral walls 61 extending from its radial and circumferentially extending edges to space the heat shield 50 from a first surface 39 of the upstream end wall 40 and to form a chamber 55 between the heat shield 50 and the upstream end wall 40. The peripheral walls 61 abut the first surface 39 of the upstream end wall 40. Each heat shield 50 also has a wall 63 extending from the perimeter of the central aperture 52 towards, but spaced from, the upstream end wall 40 to form a slot 65. The upstream end wall 40 has impingement cooling holes (not shown) extending there-through from a second surface 41 to the first surface 39 of the upstream end wall 40 to supply coolant, e.g. air, into the chambers 55 between the heat shields 50 and the upstream end wall 40 and each heat shield 50 has effusion cooling holes (not shown) extending there-through from a second surface 53 to a first surface 51 of the heat shield 50 to provide a film of coolant, e.g. air, over the first, hot, surface 51 of the heat shields 50.

[0037] The radially inner annular wall 42 may be provided with a plurality of tiles 43 spaced radially outwardly from the radially inner annular wall 42 at a greater radial distance to protect the radially inner annular wall 42 from the hot combustion gases. There may be one or more rows of circumferentially spaced tiles 43. Similarly, the radially outer annular wall 44 may be provided with a plurality of tiles 45 spaced radially inwardly from the radially outer annular wall 44 at a smaller radial distance to protect the radially outer annular wall 44 from the hot combustion gases. There may be one or more rows of circumferentially spaced tiles 45. Each tile 43, 45 is secured to the respective annular wall 42 or 44 by a plurality of threaded studs which extend from the tile 43, 45 through apertures in the respective annular wall 42 or 44 and which thread into corresponding nuts. However, the tiles 43, 45 may be secured to the annular walls 42 and 44 by other suitable arrangements.

[0038] Each fuel injector 34 comprises a fuel feed arm 54, a flange 56 and a fuel injector head 58. Each fuel injector 34 locates in a corresponding one of the apertures 38 in the annular combustion chamber casing 30 and the flange 56 of each fuel injector 34 is removably secured to the annular combustion chamber casing 30. The flange 56 of each fuel injector 34 is secured to a respective boss on the outside of the annular combustion chamber casing 30 by a plurality of bolts (not shown) which locate in threaded holes in the boss.

[0039] The fuel injector head 58 of each fuel injector 34 is located in a corresponding one of the apertures 46 in the upstream end wall 40. The fuel injector head 58 of each fuel injector 34 has an axis 60 and a plurality of coaxial passages, described below. The axis 60 of the fuel injector head 58 is arranged parallel to the axis of the annular combustion chamber casing 30, parallel to the flange 56 of the fuel injector 34 and the axis X of the turbofan gas turbine engine 10 and the axis 60 of the fuel injector head 58 is parallel to the centre line 48 of the annular combustion chamber 32. The centre line 48 of the annular combustion chamber 32 is arranged parallel to the axis of the annular combustion chamber casing 30.

[0040] FIG. 6 shows a longitudinal cross-section through the fuel injector head 58 of one of the fuel injectors 34. The fuel injectors 34 are lean burn fuel injectors. The fuel injector head 58 has a coaxial arrangement of an inner pilot airblast fuel injector and an outer mains airblast fuel injector. The pilot airblast fuel injector has, in order from radially inner to outer, a coaxial arrangement of a pilot inner swirler air passage 70, a pilot fuel passage 72, and a pilot outer air swirler passage 74. The mains airblast fuel injector has, in order from radially inner to outer, a coaxial arrangement of a mains inner swirler air passage 76, a mains fuel passage 78, and a mains outer air swirler passage 80. An intermediate air swirler passage 82 is sandwiched between the outer air swirler passage 74 of the pilot airblast fuel injector and the inner swirler air passage 76 of the mains airblast fuel injector. The swirling air passing through the passages 70, 74, 76, 80, 82 of the fuel injector head 58 is high pressure and high velocity air derived from the high pressure compressor 14. Each swirler passage 70, 74, 76, 80, 82 has a respective swirler 84, 86, 88, 90, 92 which swirls the air flow through that passage.

[0041] Each tubular seal 36 is positioned between the associated fuel injector head 58 and the corresponding aperture 46 in the upstream end wall 40 of the annular combustion chamber 32. Each tubular seal 36 comprises a flange 62 and an aperture 64 extending through the tubular seal 36 and the axis of the aperture 64 is arranged parallel to the axis 60 of the fuel injector head 58. Each tubular seal 36 is movable radially and circumferentially with respect to the axis of the annular combustion chamber casing 30. Each tubular seal 36 is also movable radially with respect to the axis of the corresponding aperture 46 in the upstream end wall 40 of the annular combustion chamber 32. The flange 62 of each tubular seal 36 locates in a groove 65 defined by the upstream end wall 40 and a corresponding one of the heat shields 50.

[0042] Each fuel injector head 58 is located in the corresponding tubular seal 36 and each fuel injector head 58 has a cylindrical, or part spherical, surface 66 and the cylindrical, or part spherical, surface 66 of each fuel injector head 58 abuts the corresponding tubular seal 36. The contact between the cylindrical, or part spherical, surface 66 of each fuel injector head 58 and the corresponding tubular seal 36 forms an air seal. The axis of the fuel injector head 58 and the axis of the aperture 64 in the tubular seal 36 are coaxial.

[0043] Each aperture 46 in the upstream end wall 40 is oval in cross-sectional shape, as seen more clearly in FIGS. 4 and 5, and each aperture 46 in the upstream end wall 40 has a major dimension M1 in a radial direction and a minor dimension M2 in a circumferential direction relative to the axis X of the annular combustion chamber casing 30 and the major dimension M1 is greater than the minor dimension M2. Each aperture 46 in the upstream end wall 40 in this example has an oval race track cross-sectional shape. Similarly, each heat shield 50 has an oval central aperture 52 which is aligned with the corresponding oval aperture 46 in the upstream end wall 40. The oval central aperture 52 in each heat shield 50 in this example has an oval race track cross-sectional shape. The central aperture 52 in each heat shield 50 has a major dimension M3 in a radial direction and a minor dimension M4 in a circumferential direction relative to the axis X of the annular combustion chamber casing 30 and the major dimension M3 is greater than the minor dimension M4. In this example the major dimensions M1 and M3 are the same and the minor dimension M2 and M4 are the same. The centre 67 of the oval aperture 52 in each heat shield 50 is aligned with the centre 37 of the corresponding oval aperture 46 in the upstream end wall 40.

[0044] It is to be noted that when the fuel injectors 34 are installed in the annular combustion chamber 32 that the axis 60 of each fuel injector head 58 and the axis of the corresponding tubular seal 36 may positioned radially inwardly of the positions of the corresponding centre 67 of the oval aperture 52 in the heat shield 50 and the corresponding centre 37 of the oval aperture 46 in the upstream end wall 40.

[0045] In order to remove a fuel injector 34, once the bolts have been removed from the flange 56 of the fuel injector 34, the fuel injector head 58 and the tubular seal are moved radially outwardly such that the axis 60 of the fuel injector head 58 and the axis of the corresponding tubular seal 36 are positioned radially outwardly of the corresponding centre 67 of the oval aperture 52 in the heat shield 50 and the corresponding centre 37 of the oval aperture 46 in the upstream end wall 40. The fuel injector 34 is then moved axially such that the fuel injector head 58 moves axially out of the corresponding tubular seal 36.

[0046] The advantage of the present disclosure is that the apertures in the upstream end wall of the annular combustion chamber are not circular but are oval with their major dimensions arranged radially such that it is not necessary to increase the diameter of the apertures in the upstream end wall and hence the distances and the amount of material between the aperture in the upstream end wall is not reduced and the strength of the upstream end wall is not reduced and the space available to provide impingement cooling holes in the upstream end wall is not reduced. Similarly, the central apertures in the heat shields of the annular combustion chamber are not circular but are oval with their major dimensions arranged radially such that it is not necessary to increase the diameter of the apertures in the heat shields and hence the distances and the amount of material between the aperture in the heat shields the peripheral walls is not reduced and the space available to provide effusion cooling holes in the heat shields is not reduced. Thus, the present disclosure increases the tubular seal clearance to enable lean burn fuel injectors to be installed and/or removed from the tubular seals located in the upstream end wall of the combustion chamber whilst minimising the amount of material, metal, removed from the upstream end wall and the heat shields. The working life of the heat shields used with lean burn fuel injectors is increased by maximising the cooling of the heat shields.

[0047] A further combustion chamber assembly 115 is shown more clearly in FIG. 7 and the combustion chamber assembly 115 is substantially the same as that shown in FIGS. 2 to 6 and comprises an annular combustion chamber casing 30, an annular combustion chamber 32, a plurality of fuel injectors 34 and a plurality of tubular seals 36. The combustion chamber assembly 115 differs in that the annular combustion chamber 32 and the centre line 48 of the combustion chamber 32 are arranged at an acute angle α to the axis of the annular combustion chamber casing 30 and the axis X of the turbofan gas turbine engine 10. Thus, it can be seen that in this arrangement the upstream end wall 40 is frusto-conical, e.g. the upstream end wall 40 is arranged on a part conical surface. In this arrangement, the axis 60 of each fuel injector head 58 is arranged at the acute angle a to the axis of the annular combustion chamber casing 30 and the axis X of the turbofan gas turbine engine 10 and the axis 60 of each fuel injector head 58 is parallel to the centre line 48 of the annular combustion chamber 32. The axis of each tubular seal 36 is arranged at the acute angle a to the axis of the annular combustion chamber casing 30 and the axis X of the turbofan gas turbine engine 10 and the axis of each tubular seal 36 is arranged parallel to the centre line 48 of the annular combustion chamber 32.

[0048] Again, in order to remove a fuel injector 34, once the bolts have been removed from the flange 56 of the fuel injector 34, the fuel injector head 58 and the tubular seal are moved radially outwardly such that the axis 60 of the fuel injector head 58 and the axis of the corresponding tubular seal 36 are positioned radially outwardly of the corresponding centre 67 of the oval aperture 52 in the heat shield 50 and the corresponding centre 37 of the oval aperture 46 in the upstream end wall 40. The fuel injector 34 is then moved axially such that the fuel injector head 58 moves axially out of the corresponding tubular seal 36.

[0049] The at least one aperture may have a corresponding locating ring and the locating ring having an oval aperture extending there-through. The oval aperture in the locating ring may be race track shaped. The locating ring may be aligned with the at least one aperture in the upstream end wall. The locating ring may be positioned axially between the flange of the tubular seal and an upstream surface of the upstream end wall. The locating ring may be positioned within the at least one aperture in the upstream end wall.

[0050] A combustion chamber assembly with an alternative upstream end wall 140 arrangement is shown in FIG. 8. The upstream end wall 140 has first and second surfaces 139 and 141 and an oval aperture 146. Each heat shield 150 has first and second surface 151 and 153 and an oval aperture 152. A chamber 155 is formed between each heat shield 150 and the upstream end wall 140. Each tubular seal 136 is positioned in a corresponding one of the oval apertures 146 in the upstream end wall 140 and in an oval central aperture 152 in the corresponding heat shield 150. The flange 162 of each tubular seal 136 is located axially in a groove 165 defined between a first oval locating ring 168 and a second oval locating ring 170. The first oval locating ring 168 is located radially between the peripheral wall 163 around the oval central aperture 152 of the heat shield 150 and the upstream end wall 140. The second oval locating ring 170 is Z-shaped in cross-section and comprises a first portion, an axially central portion and a third portion. The first portion extends radially outwardly from the downstream end of the axially central portion and hooks onto the upstream end wall 140 and the third portion extends radially inwardly from the upstream end of the axially central portion to hook over the flange 162 of the tubular seal 136. The heat shields 150 have effusion cooling apertures 172 extending there-through from their first surfaces 151 to their second surfaces 153 and pedestals 174 extending from their second surfaces 153.

[0051] A further combustion chamber assembly with an alternative upstream end wall 240 arrangement is shown in FIG. 9. The upstream end wall 240 has first and second surfaces 239 and 241 and an oval aperture 246. Each heat shield 250 has first and second surface 251 and 253 and an oval aperture 252. A chamber 255 is formed between each heat shield 250 and the upstream end wall 240. Each tubular seal 236 is positioned in a corresponding one of the oval apertures 246 in the upstream end wall 240 and in an oval central aperture 252 in the corresponding heat shield 250. The flange 262 of each tubular seal 236 is located axially in a groove 265 defined between a first oval locating ring 268 and the upstream end wall 240. The upstream end wall 240 has an oval locating hook 270 which comprises a first portion which extends axially from the second surface 141 and a second portion which extends radially inwards from the upstream end of the first portion to hook over the first oval locating ring 270. The peripheral wall 263 around the oval central aperture 252 of the heat shield 250 abuts the upstream end wall 240. The heat shields 250 have effusion cooling apertures 272 extending there-through from their first surfaces 251 to their second surfaces 253 and pedestals 274 extending from their second surfaces 253.

[0052] Another combustion chamber assembly with an alternative upstream end wall 340 arrangement is shown in FIG. 10. The upstream end wall 340 has first and second surfaces 339 and 341 and an oval aperture 346. Each heat shield 350 has first and second surface 351 and 353 and an oval aperture 352. A chamber 355 is formed between each heat shield 350 and the upstream end wall 340. Each tubular seal 336 is positioned in a corresponding one of the oval apertures 346 in the upstream end wall 340 and in an oval central aperture 352 in the corresponding heat shield 350. Each tubular seal 336 extends axially through the oval aperture 246 in the upstream end wall 340 and through the oval aperture 352 in a corresponding one of the heat shields 350. Each tubular seal 336 is trapped in the corresponding heat shield 350 due to the upstream and downstream ends of the tubular seal 336 extending radially outwards and the heat shield 350 and tubular seal 336 are manufactured together by additive layer manufacturing. The peripheral wall 363 around the oval central aperture 352 of the heat shield 350 extends upstream and into the oval aperture 346 of the upstream end wall 340. The heat shields 350 have effusion cooling apertures 372 extending there-through from their first surfaces 351 to their second surfaces 353 and pedestals 374 extending from their second surfaces 353.

[0053] A locating ring may have an oval shaped aperture and an oval shaped outer surface, the locating ring aligning with the oval shaped aperture in the upstream end wall and a heat shield having an oval shaped aperture aligning with the aperture in the upstream end wall. The locating ring may locate in the oval shaped aperture in the upstream end wall.

[0054] The combustion chamber assembly may have guide features provided on the tubular seal and corresponding guide features provided on adjacent structure such that the tubular seal moves radially with respect to the combustion chamber. The tubular seal may be movable radially with respect to the axis of the annular combustion chamber casing. The corresponding guide features may be provided on the locating ring, the heat shield or the upstream end wall.

[0055] The at least one combustion chamber may be an annular combustion chamber, the upstream end wall having a plurality of circumferentially spaced apertures extending there-through, each aperture in the upstream end wall being oval in cross-sectional shape, each aperture in the upstream end wall having a major dimension in a radial direction and a minor dimension in a circumferential direction relative to the axis of the annular combustion chamber casing and the major dimension of each aperture being greater than the minor dimension of the respective aperture.

[0056] The axis of the fuel injector head may be arranged at an angle to the axis of the annular combustion chamber casing and/or at an angle to the flange of the fuel injector and parallel to the centre line of the at least one combustion chamber.

[0057] The at least one combustion chamber may be a tubular combustion chamber.

[0058] Although the present disclosure has been described with reference to lean burn fuel injectors it is equally applicable to rich burn fuel injectors, especially if they have relatively large outside diameter and a relatively large axial length.

[0059] Although the present disclosure has been described with reference to a turbofan gas turbine engine it is equally applicable to a turbojet gas turbine engine, a turbo-propeller gas turbine engine or a turbo-shaft gas turbine engine.

[0060] Although the present disclosure has been described with reference to an aero gas turbine engine it is equally applicable to a marine gas turbine engine, an automotive gas turbine engine or an industrial gas turbine engine.

[0061] It will be understood that the invention is not limited to the embodiments above-described and various modifications and improvements can be made without departing from the concepts described herein. Except where mutually exclusive, any of the features may be employed separately or in combination with any other features and the disclosure extends to and includes all combinations and sub-combinations of one or more features described herein.