COMBUSTION CHAMBER ASSEMBLY WITH COLLAR SECTION AT A MIXING AIR HOLE OF A COMBUSTION CHAMBER SHINGLE

Abstract

A combustion chamber assembly includes a through hole on the combustion chamber wall bounded on an outer side of the wall by a hole edge and a combustion chamber shingle having a collar bounding a mixing air hole on the outer side of the wall and protruding with a first collar portion beyond the hole edge on the outer side of the wall. A cooling air opening is formed on an inner circumferential surface of a duct portion of the mixing air hole adjoining the first collar portion and extending in the direction of a combustion space, the cooling air opening leading into a cooling air duct which extends through the duct portion and via which cooling air is guided out of the mixing air hole in a direction of a hot side of the shingle facing the combustion space.

Claims

1. A combustion chamber assembly, having a combustion chamber for an engine, the combustion chamber comprising a combustion chamber wall which at least partially surrounds a combustion space of the combustion chamber and has at least one through hole, and at least one combustion chamber shingle which is fixed on an inner side of the combustion chamber wall and has a mixing air hole for guiding mixing air into the combustion space, the through hole being bounded on an outer side of the combustion chamber wall by a hole edge and the combustion chamber shingle having a collar which bounds the mixing air hole on the outer side of the combustion chamber wall and protrudes with at least one first collar portion beyond the hole edge on the outer side of the combustion chamber wall, wherein at least one cooling air opening is formed on an inner circumferential surface of a duct portion of the mixing air hole adjoining the first collar portion and extending in the direction of the combustion space, the cooling air opening leading into a cooling air duct which extends through the duct portion and via which cooling air can be guided out of the mixing air hole in the direction of a hot side of the combustion chamber shingle facing the combustion space.

2. The combustion chamber assembly according to claim 1, wherein the duct portion extends along a direction of extent and the cooling air duct runs in the duct portion at an inclination with respect to the direction of extent.

3. The combustion chamber assembly according to claim 1, wherein the at least one cooling air opening has a droplet-shaped or elliptical cross section.

4. The combustion chamber assembly according to claim 1, wherein the duct portion extends along a direction of extent and the at least one cooling air opening is provided on a region of the circumferential surface that adjoins the first collar portion in the direction of extent.

5. The combustion chamber assembly according to claim 1, wherein a plurality of cooling air openings are formed on the inner circumferential surface of the duct portion, the cooling air openings each leading into an associated cooling air duct.

6. The combustion chamber assembly according to claim 4, wherein the plurality of cooling air openings are each provided in a region of the circumferential surface that adjoins the first collar portion in the direction of extent.

7. The combustion chamber assembly according to claim 1, wherein the collar of the combustion chamber shingle that bounds the mixing air hole on the outer side of the combustion chamber wall has at least one second collar portion which does not protrude beyond the hole edge on the outer side of the combustion chamber wall.

8. Combustion chamber assembly according to claim 7, wherein a cooling air opening is not provided on the circumferential surface on a region of the duct portion that adjoins the second collar portion in the direction of extent.

9. The combustion chamber assembly according to claim 7, wherein the second collar portion merges continuously into the first collar portion.

10. The combustion chamber assembly according to claim 7, wherein at least one region of the second collar portion is set back in relation to the hole edge.

11. The combustion chamber assembly according to claim 7, wherein at least the collar of the combustion chamber shingle that bounds the mixing air hole is produced additively, specifically along a manufacturing direction pointing from the second collar portion to the first collar portion.

12. The combustion chamber assembly according to claim 1, wherein the first collar portion protruding over the hole edge extends over at least a fifth and/or over a maximum of three-fifths of a circumference of the mixing air hole.

13. The combustion chamber assembly according to claim 1, wherein the duct portion of the mixing air hole forms a further protruding collar at an end projecting into the combustion space.

14. The combustion chamber assembly according to claim 1, wherein at least one positioning portion for predetermining a certain position of the collar in the through hole is provided on the collar bounding the mixing air hole on the outer side of the combustion chamber wall.

15. The combustion chamber assembly according to claim 14, wherein the at least one positioning portion is formed on an outer circumferential surface of the collar bounding the mixing air hole on the outer side of the combustion chamber wall, and protrudes in the direction of an inner circumferential surface of the through hole.

16. The combustion chamber assembly according to claim 14, wherein at least two spaced-apart positioning portions are formed on the collar bounding the mixing air hole on the outer side of the combustion chamber wall.

17. The combustion chamber assembly according to claim 1, wherein a base which projects in the direction of the inner side of the combustion chamber wall and from which the collar bounding the mixing air hole on the outer side of the combustion chamber wall protrudes is formed on a cold side of the combustion chamber shingle that faces the inner side of the combustion chamber wall.

18. The combustion chamber assembly according to claim 17, wherein a step is formed at a transition from the projecting base to the collar bounding the mixing air hole on the outer side of the combustion chamber wall.

19. A gas turbine engine having a combustion chamber which has at least one combustion chamber assembly according to claim 1.

Description

[0029] The appended figures illustrate, by way of example, possible embodiment variants of the proposed solution.

[0030] In the figures:

[0031] FIG. 1 shows, in detail, an embodiment variant of a proposed combustion chamber assembly having a mixing air hole on a combustion chamber shingle, said mixing air hole being bounded both on a cold side and on a hot side by an encircling collar;

[0032] FIG. 2 shows, in an enlarged illustration and in detail, the combustion chamber shingle looking at the cold side and the collar, on the cold side, which is formed with a circumferentially variable height, and therefore, in the mounted state, a first duct portion protrudes over a hole edge of a through hole of the combustion chamber wall according to FIG. 1 and a second collar portion extends at maximum as far as said hole edge;

[0033] FIG. 3A shows a schematic sectional illustration of a gas turbine engine in which a proposed combustion chamber assembly is used;

[0034] FIG. 3B shows a schematic sectional illustration of a combustion chamber of the gas turbine engine of FIG. 3A;

[0035] FIG. 3C shows, in detail, an enlarged sectional illustration of a combustion chamber with a combustion chamber shingle.

[0036] FIG. 3A illustrates, schematically and in a sectional illustration, a (turbofan) engine T in which the individual engine components are arranged one behind the other along an axis of rotation or central axis M, and the engine T is formed as a turbofan engine. At an inlet or intake E of the engine T, air is drawn in along an inlet direction by means of a fan F. This fan F, which is arranged in a fan casing FC, is driven by means of a rotor shaft S which is set in rotation by a turbine TT of the engine T. The turbine TT here adjoins a compressor V, which has, for example, a low-pressure compressor 111 and a high-pressure compressor 112, and optionally also a medium-pressure compressor. On the one hand, the fan F conducts air in a primary airflow F1 to the compressor V, and, on the other hand, to generate thrust, in a secondary air flow F2 to a secondary flow duct or bypass duct B. The bypass duct B here runs around a core engine comprising the compressor V and the turbine TT and comprising a primary flow duct for the air supplied to the core engine by the fan F.

[0037] The air fed into the primary flow duct via the compressor V enters a combustion chamber BK of the core engine, in which the driving energy for driving the turbine TT is generated. For this purpose, the turbine TT has a high-pressure turbine 113, a medium-pressure turbine 114 and a low-pressure turbine 115. Here, the energy released during the combustion is used by the turbine TT to drive the rotor shaft S and thus the fan F in order to generate the required thrust by means of the air conveyed into the bypass duct B. Both the air from the bypass duct B and the exhaust gases from the primary flow duct of the core engine flow out via an outlet A at the end of the engine T. In this arrangement, the outlet A generally has a thrust nozzle with a centrally arranged outlet cone C.

[0038] FIG. 3B shows a longitudinal section through the combustion chamber portion BK of the engine T. The combustion chamber BK is designed here as an annular combustion chamber which forms part of an embodiment variant of a proposed combustion chamber assembly. A nozzle assembly is provided for the injection of fuel or an air-fuel mixture into a combustion space 30 of the combustion chamber BK. Said nozzle assembly comprises a combustion chamber ring, on which multiple fuel nozzles 2 are arranged along a circular line around the central axis M. Here, on the combustion chamber ring, there are provided the nozzle outlet openings of the respective fuel nozzles 2 which are situated within the combustion chamber BK. Here, each fuel nozzle 2 comprises a flange by means of which a fuel nozzle 2 is screwed to an outer casing 22.

[0039] A configuration of the combustion chamber BK is illustrated in more detail in the enlarged sectional illustration of FIG. 3C. The combustion chamber BK here comprises the fuel nozzle 2 which is held in a combustion chamber head. Fuel is injected into the combustion space 30 of the combustion chamber BK via the fuel nozzle 2. The exhaust gases of the mixture ignited within the combustion space 30 pass in an axial direction x via a turbine inlet guide vane row 33 to the high-pressure turbine 113 in order to set the turbine stages into rotation.

[0040] The combustion space 30 is delimited by, with respect to the central axis M of the engine T, radially inner and radially outer combustion chamber walls 32a, 32b of a combustion chamber housing of the combustion chamber BK, said walls each extending firstly along the axial direction x and secondly along a circumferential direction about said axial direction x. The combustion chamber walls 32a and 32b therefore extend firstly along the axial direction x along the central axis M and along the circumferential direction. A radial direction r runs perpendicularly both to the axial direction x and to the circumferential direction. Air, for example, flows along said radial direction r into the combustion space 3 via admixing holes 35.

[0041] Combustion chamber shingles 34a, 34b are arranged on the inner side of the combustion chamber walls 32a, 32b. The combustion chamber walls 32a, 32b therefore surround the combustion space 30 of the combustion chamber BK and support the combustion chamber shingles 34a, 34b with which the combustion chamber walls 32a, 32b are covered in order to permit additional cooling and to withstand the high temperatures prevailing within the combustion space 30.

[0042] The combustion chamber shingles 34a, 34b are each held here on the respective inner or outer combustion chamber wall 32a, 32b via one or more bolts 4. Each bolt 4 reaches here through an opening on the combustion chamber wall 32a or 32b and is fixed on the combustion chamber wall 32a or 32b via a respective nut 5. For example, via a plurality of effusion cooling holes provided on a combustion chamber shingle 34a or 34b, cooling of the respective combustion chamber shingle 34a or 34b is permitted. In addition, a combustion chamber shingle 34a, 34b can have at least one admixing hole 35 via which air can flow into the combustion space 30 from a surrounding exterior space. The air flowing via an admixing hole 35 serves for the cooling and/or the leaning of the combustion.

[0043] The exterior space surrounding the combustion chamber BK, for example in the form of an annular duct, forms an air supply 36 for the admixing holes 35 (and possible effusion cooling holes). Air flowing into the combustion chamber BK along an inflow direction Z is divided here in the region of the fuel nozzle 2 via a portion configured in the manner of a hood into a primary air flow for the combustion space 30 and a secondary air flow for the surrounding exterior space with the air supply 36. The air conventionally flows here into the combustion chamber BK via a diffuser (not illustrated).

[0044] FIGS. 1 and 2 each show, in detail, in different enlarged illustrations, details of an embodiment variant of a proposed combustion chamber assembly, in which a combustion chamber shingle 34a, 34b has a collar 350 bounding a mixing air hole 35 on the outer side of the combustion chamber wall 32a, 32b. Said collar 350 has a first collar portion 3501 which protrudes on the outer side of the combustion chamber wall 32a, 32b beyond a hole edge 3201 of a through hole 320 on the combustion chamber wall, in which the collar 350 on the combustion chamber shingle is accommodated. Consequently, the collar 350 of the combustion chamber shingle 34a, 34b protrudes at least with the first collar portion 3501 beyond the hole edge 3201 on the outer side of the combustion chamber wall 32a, 32b.

[0045] The collar 350, in addition to the first collar portion 3501 protruding beyond the hole edge 3201, also has a second collar portion 3502 which lies below the hole edge 3201 (cf. in particular FIG. 1) and consequently extends at maximum as far as said hole edge 3201. The second collar portion 3502 lies upstream of the first collar portion 3501 with respect to a direction of flow of air flowing along the outer side of the combustion chamber wall 32a or 32b during operation of the engine. In this way, air can flow on the outer side of the combustion chamber wall at least in part beyond the second collar portion 3502 to the first collar portion 3501 protruding over the hole edge 3201, where the air is deflected via said first collar portion 3501 (to a greater extent) into the mixing air hole 35. On the upstream second collar portion 3502, at least one local recess is formed with respect to the hole edge 3201, via which, however, the admission of an airflow into the mixing air hole 35 is likewise assisted.

[0046] As is shown in particular by way of the detailed illustration in FIG. 2, the collar portions 3501 and 3502 merge continuously into one another, wherein the first collar portion 3501 extends over approximately half of the circumference of the mixing air hole 35.

[0047] The collar 350, on the cold side, is adjoined in the radial direction r by a duct portion of the mixing air hole 35, the duct portion defining an inner circumferential surface 352. In a region of said circumferential surface 352 adjoining the first collar portion 3501 here directly in the radial direction r and thus in the direction of extent of the duct portion, a plurality of (here eight or nine) cooling air openings 3520 are formed on the inner circumferential surface 352 in a manner spaced apart from one another on the inner circumferential surface 352. Via said cooling air openings 3520 which are present below the first collar portion 3501 in the illustration of FIGS. 1 and 2, air can pass out of the mixing air hole 35 into cooling air ducts 3521 in the duct portion of the mixing air hole 35. Each cooling air opening 3520 is assigned precisely one cooling air duct 3521 here. Each cooling air duct 3521 runs here at an inclination with respect to the radial direction r and therefore at an inclination with respect to the direction of extent of the mixing air hole 35 within the duct portion, for example at an inclination by an angle of approximately 60°. A cooling air duct 3521 ends here on the hot side of the combustion chamber shingle 34a, 34b facing the combustion space. Cooling air can therefore be guided out of the mixing air hole 35 to the hot side of the combustion chamber shingle 34a, 34b via the cooling air openings 3520 and the cooling air ducts 3521 thereof. By means of the arrangement in the immediate spatial vicinity of the protruding first collar portion 3501, the supply of cooling air into the cooling air openings 3520 is assisted here.

[0048] Via the cooling air openings 3520 and the associated cooling air ducts 3521 thereof, use is therefore made of some of the mixing air flow in order to guide a cooling air flow to the hot side of the combustion chamber shingle 34a, 34b. The first collar portion 3501 protruding over the hole edge 3201 therefore not only permits an improved “trapping” and deflection of air flowing on the outer side of the combustion chamber wall 32a, 32b into the respective mixing air hole 35. On the contrary, this also—in combination with the cooling air openings 3520 on the mixing air hole side—makes an improved cooling air flow to the hot side of the combustion chamber shingle 34a, 34b possible. For the cooling of the cold side of the combustion chamber shingle 34a, 34b facing the inner side of the combustion chamber wall 32a, 32b, the combustion chamber wall 32a, 32b in turn has a multiplicity of cooling air holes 321.

[0049] The cooling air openings 3520 each have a droplet-shaped or elliptical cross section extending longitudinally here in the radial direction r. Such a cross section is advantageous for additive manufacturing of the combustion chamber shingle 34a, 34b and in particular of the protruding collar 350. The collar 350 is thus produced additively along a manufacturing direction R, for example according to FIG. 2, and therefore the second collar portion 3502 can form a supporting structure for the first collar portion 3501 during the additive manufacturing process.

[0050] The external dimensions of the collar 352 protruding into the through hole 320 on the combustion chamber wall are smaller here than the dimensions of the through hole 320. In order nevertheless to permit exact positioning of the collar 350 here in the through hole 320, at least two positioning portions 3451 and 3452 are formed on the collar 350. Via said two positioning portions 3451 and 3452, the position of the collar 350 within the through hole 320 is determined along two spatial directions in the plane of the through hole 320. For this purpose, the positioning portions 3451 and 3452 are arranged offset by 90° to one another on an outer circumferential surface of the collar 350 and here in particular on an outer circumferential surface of the first collar portion 3501 and are each designed as local thickened portions which project in the direction of an inner surface of the through hole 320. In the correctly mounted state of the combustion chamber shingle 34a, 34b, a respective positioning portion 3451, 3452 can therefore lie against the inner circumferential surface of the through hole 320 and can therefore predetermine a certain position and therefore orientation for the collar 350 within the through hole 320.

[0051] The outer circumferential surface of the collar 350 is set back here in relation to a step 3450 which is formed at a transition of the collar 350 to a base 345 protruding on the cold side of the combustion chamber shingle. Said base 345 is formed in a manner protruding on a shingle base surface 340 of the combustion chamber shingle 34a, 34b in the direction of the inner side of the combustion chamber wall 32a, 32b and supports the collar 350 which therefore extends further, starting from the base 345, into the through hole 320 of the combustion chamber wall 32a, 32b.

[0052] In addition to the collar 350, on the cold side, with the collar portions 3501 and 3502 protruding to differing extents, the combustion chamber shingle 34a, 34b illustrated in FIGS. 1 and 2 also has a (further) collar 351 on the hot side at the end of the duct portion of the mixing air hole 35. Said collar 351, on the hot side, therefore protrudes at least slightly on the hot side of the combustion chamber shingle 34a, 34b and defines an outlet opening, which protrudes in relation to adjacent portions of the combustion chamber shingle 34a, 34b, for mixing air which is guided into the combustion space 30 via the mixing air hole 35. By this means, a more targeted inflow of the mixing air into a certain zone of the combustion space 30 is possible. The inflowing mixing air can also be separated to a greater extent from the air guided via the cooling air openings 3520 and the cooling air ducts 3521 thereof additionally to the hot side of the combustion chamber shingle 34a, 34b.

LIST OF REFERENCE SIGNS

[0053] 111 Low-pressure compressor [0054] 112 High-pressure compressor [0055] 113 High-pressure turbine [0056] 114 Medium-pressure turbine [0057] 115 Low-pressure turbine [0058] 2 Fuel nozzle [0059] 22 Outer housing [0060] 30 Combustion space [0061] 32a, 32b Inner/outer combustion chamber wall [0062] 320 Through hole [0063] 3201 Hole edge [0064] 321 Cooling air hole [0065] 33 Turbine inlet guide vane row [0066] 34a, 34b Inner/outer combustion chamber shingle [0067] 340 Shingle base surface [0068] 345 Base [0069] 3450 Step [0070] 3451, 3452 Positioning portion [0071] 35 Admixing hole/mixing air hole [0072] 350 Collar, on the cold side [0073] 3501 First collar portion [0074] 3502 Second collar portion [0075] 351 Collar, on the hot side [0076] 352 Inner circumferential surface [0077] 3520 Cooling air opening [0078] 3521 Cooling air duct [0079] 36 Air supply [0080] 4 Bolt [0081] 5 Nut [0082] A Outlet [0083] B Bypass duct [0084] BK Combustion chamber [0085] C Outlet cone [0086] E Inlet/Intake [0087] F Fan [0088] F1, F2 Fluid flow [0089] FC Fan casing [0090] M Central axis/Axis of rotation [0091] r Radial direction/direction of extent [0092] R Manufacturing direction [0093] S Rotor shaft [0094] T (Turbofan) engine [0095] TT Turbine [0096] V Compressor [0097] x Axial direction [0098] Z Inflow direction