Combustion chamber assembly with shingle part and positioning facility

Abstract

A combustion chamber assembly for an engine with at least one tile component, on the cold side of which facing away from a combustion space, a positioning aid with at least two positioning elements, wherein a defined position relative to the combustion chamber component is predefined for the tile component via the contact of the at least two positioning elements on at least one contact face of the combustion chamber component in two spatial axes.

Claims

1. A combustion chamber assembly for an engine, comprising: a combustor dome and a combustion chamber wall which is annular and surrounds a combustion space, and a tile component fixed on the combustion chamber wall and having a hot side facing the combustion space and a cold side facing away from the combustion space and towards the combustion chamber wall, wherein the tile component includes at least one air passage opening having a first axis and a first edge protruding in a direction toward the combustion chamber wall, and on the cold side at least one fixing element for fixing the tile component to the combustion chamber wall, wherein the combustion chamber wall includes at least one fixing opening for the at least one fixing element and at least one air supply opening with which the at least one air passage opening of the tile component is aligned, the at least one air supply opening including at least one contact face, at least two positioning elements positioned on the cold side of the tile component, wherein a defined position relative to the combustion chamber wall is predefined for the tile component via a contact of the at least two positioning elements on the at least one contact face of the combustion chamber wall in two spatial axes; wherein the first edge protruding in the direction toward the combustion chamber wall extends inside of the at least one air supply opening, the first edge including a first positioning element of the at least two positioning elements that protrudes radially, with respect to the first axis and only partially around a circumference of the first edge, from the first edge toward the at least one contact face to engage the at least one contact face to obtain the defined position of the tile component with respect to the combustion chamber wall.

2. The combustion chamber assembly according to claim 1, wherein the two spatial axes run perpendicularly to an attachment direction in which the tile component is mounted on the combustion chamber wall.

3. The combustion chamber assembly according to claim 2, wherein a first spatial axis of the two spatial axes extends tangential to a circumferential direction of the combustion chamber assembly, and a second spatial axis of the two spatial axes extends in a flow direction in which fluid flows in the direction of an outlet from the combustion space during operation of the engine.

4. The combustion chamber assembly according to claim 1, wherein the at least one fixing element includes a plurality of fixing elements and the at least one fixing opening includes a plurality of fixing openings to respectively receive the plurality of fixing elements.

5. The combustion chamber assembly according to claim 1, wherein the first edge includes a second positioning element of the at least two positioning elements that protrudes radially, with respect to the first axis and only partially around a circumference of the first edge, from the first edge toward the at least one contact face to engage the at least one contact face to obtain the defined position of the tile component with respect to the combustion chamber wall, the second positioning element being circumferentially spaced around the first edge from the first positioning element.

6. The combustion chamber assembly according to claim 1, wherein the first positioning element is positioned to protrude locally in a first spatial axis of the two spatial axes, and the second positioning element is positioned to protrude locally in a second spatial axis of the two spatial axes.

7. The combustion chamber assembly according to claim 1, wherein the at least one air passage opening includes two air passage openings, and each of the two air passage openings includes at least one of the at least two positioning elements that engages the at least one contact face.

8. The combustion chamber assembly according to claim 1, wherein the at least one fixing element includes a plurality of fixing elements and the at least one fixing opening includes a plurality of fixing openings to respectively receive the plurality of fixing elements, with a first fixing element of the plurality of fixing elements being positioned in a central region of the tile component, and the first positioning element protruding toward the first fixing element.

9. The combustion chamber assembly according to claim 8, wherein the at least one air passage opening includes two air passage openings which have different distances from the first fixing element, and the first positioning element and a second positioning element of the at least two positioning elements are both provided on the first edge, the first edge being an edge of one of the two air passage openings that is closest to the first fixing element.

10. The combustion chamber assembly according to claim 1, wherein the at least one contact face includes at least one positioning recess for receiving the first positioning elements.

11. The combustion chamber assembly according to claim 10, wherein the at least one positioning recess is positioned at an edge of the at least one air supply opening.

12. The combustion chamber assembly according to claim 1, and further comprising at least one positioning opening positioned in the combustion chamber wall spaced apart from the at least one air passage opening and the at least one fixing element, wherein at least one of the at least two positioning elements is positioned in the at least one positioning opening.

13. The combustion chamber assembly according to claim 12, wherein the at least one positioning opening includes two positioning openings respectively receiving one of the at least two positioning elements.

14. The combustion chamber assembly according to claim 13, wherein a first positioning opening of the two positioning openings has a circular cross-section, and a second positioning opening of the two positioning openings has a rectangular cross-section.

15. An engine with the combustion chamber assembly according to claim 1.

16. A method for producing a combustion chamber assembly for an engine comprising at least the following steps: providing a combustion chamber structure including a combustor dome and a combustion chamber wall which is annular and surrounds a combustion space, and providing a tile component to be fixed on the combustion chamber wall and having a hot side which, in a mounted state, faces the combustion space, and a cold side which, in a mounted state, faces away from the combustion space and towards the combustion chamber wall, providing that the tile component comprises at least one air passage opening having a first axis and a first edge protruding in a direction toward the combustion chamber wall, and on the cold side at least one fixing element for fixing the tile component to the combustion chamber wall, providing that the combustion chamber wall has at least one fixing opening for the at least one fixing element and at least one air supply opening with which the at least one air passage opening of the tile component is aligned, the at least one air supply opening including at least one contact face when the tile component is mounted on the combustion chamber wall, providing at least two positioning elements on the cold side of the tile component, wherein a defined position relative to the combustion chamber wall is predefined for the tile component, when mounted on the combustion chamber wall, via a contact of the at least two positioning elements on the at least one contact face of the combustion chamber wall in two spatial axes, before the tile component is fixed to the combustion chamber wall, providing that the first edge protruding in the direction toward the combustion chamber wall extends inside of the at least one air supply opening, the first edge including a first positioning element of the at least two positioning elements that protrudes radially, with respect to the first axis and only partially around a circumference of the first edge, from the first edge toward the at least one contact face to engage the at least one contact face to obtain the defined position of the tile component with respect to the combustion chamber wall.

Description

(1) The appended figures illustrate exemplary possible design variants of the proposed solution.

(2) In the figures:

(3) FIG. 1A shows a view onto a cold side of the tile component in the form of a combustion chamber tile according to the proposed solution, in a single view;

(4) FIG. 1B shows the combustion chamber tile from FIG. 1A in the state mounted on a combustion chamber wall, with a view from the outside of the combustion chamber wall (shown transparently);

(5) FIG. 2 shows an alternative embodiment variant of a combustion chamber tile in mounted state, in a view corresponding to FIG. 1B;

(6) FIG. 3 shows a further embodiment variant of a mounted combustion chamber tile, in a view corresponding to FIGS. 1B and 2;

(7) FIG. 4 shows an engine in which a combustion chamber assembly corresponding to FIGS. 1A to 10 is used;

(8) FIG. 5 shows, in extract and on an enlarged scale, the combustion chamber of the engine of FIG. 4;

(9) FIG. 6 shows in cross-sectional view the fundamental structure of a combustion chamber from the prior art, again on an enlarged scale in comparison with FIG. 5.

(10) FIG. 4 illustrates, schematically and in a sectional illustration, an 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. Here, the turbine TT adjoins a compressor V, which comprises for example a low-pressure compressor 111 and a high-pressure compressor 112, and possibly also a medium-pressure compressor. The fan F on one side conducts air in a primary air flow F1 to the compressor V, and on the other side, to generate thrust, in a secondary air flow F2 to a secondary flow channel or bypass channel B. The bypass channel B here runs around a core engine comprising the compressor V and the turbine TT and comprising a primary flow channel for the air supplied to the core engine by the fan F.

(11) The air conveyed into the primary flow channel by means of the compressor V passes into a combustion chamber portion BKA of the core engine, in which the drive 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 channel B. Both the air from the bypass channel B and the exhaust gases from the primary flow channel 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.

(12) In principle, the fan F can also be coupled, via the rotor shaft S and an additional epicyclic planetary gear mechanism, to the low-pressure turbine 115 and can be driven by the latter. It is furthermore also possible to provide other gas turbine engines of different configurations in which the proposed solution can be used. For example, engines of this type may have an alternative number of compressors and/or turbines and/or an alternative number of rotor shafts. By way of example, the gas turbine engine can have a split flow nozzle, meaning that the flow through the bypass channel B has its own nozzle that is separate from and radially outside the core engine nozzle. However, this is not limiting, and any aspect of the present disclosure may also apply to engines in which the flow through the bypass channel B and the flow through the core are mixed or combined before (or upstream of) a single nozzle, which may be referred to as a mixed-flow nozzle. One or both nozzles (whether mixed flow or split flow) may have a fixed or variable region. Whilst the described example relates to a turbofan engine, the proposed solution may be applied, for example, to any type of gas turbine engine, such as an open-rotor (in which the fan stage is not surrounded by a nacelle) or turboprop engine, for example.

(13) FIG. 5 shows a longitudinal section through the combustion chamber portion BKA of the engine T. This shows in particular an (annular) combustion chamber BK of the engine T. A nozzle assembly is provided for the injection of fuel or an air-fuel mixture into a combustion space 23 of the combustion chamber BK. Said nozzle assembly comprises a combustion chamber ring, on which multiple fuel nozzles 17 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 17 which are situated within the combustion chamber BK. Here, each fuel nozzle 17 comprises a flange by means of which a fuel nozzle 17 is screwed to an outer casing 22 of the combustion chamber portion BKA.

(14) FIG. 6, in a further enlarged scale compared with FIG. 5 and in sectional view, shows a combustion chamber BK known from the prior art and in particular the configuration provided here of a burner seal 4 and a heat shield 2 in the region of a combustion chamber head 3 of the combustion chamber BK. The illustrated combustion chamber BK is in this case for example a (fully) annular combustion chamber such as is used in gas turbine engines.

(15) The combustion chamber BK is arranged in the interior of the outer casing 22. The combustion chamber BK comprises, as combustion chamber components, a combustion chamber structure surrounding the combustion space 23, (radially) outer and (radially) inner combustion chamber walls 1a and 1b. These combustion chamber walls 1a, 1b are, depending on construction, shielded from the combustion space 23 in some cases with tile components in the form of combustion chamber tiles 6. These combustion chamber tiles 6 may for example each be connected to the inner and outer combustion chamber walls 1a, 1b by means of fixing elements in the form of bolts 10 and nuts 11. The combustion chamber walls 1a and 1b normally have cooling holes 12 and supply openings in the form of mixing air holes 7. A combustion chamber tile 6 may also be provided with effusion cooling holes 13. An outer combustion chamber wall 1a is connected to the outer casing 22 via an arm 8 and a flange 9.

(16) A combustion chamber head 3, with a further combustion chamber component of the combustion chamber structure in the form of a head plate 5, is provided in a front end of the combustion chamber BK relative to a longitudinal axis L. The outer and inner combustion chamber walls 1a and 1b are connected together via this combustion chamber head 3 and the head plate 5. The head plate 5 shown here comprises cooling holes 15. Furthermore, a supply opening 26 is formed on the head plate 5 which provides access to the combustion space 23 and in which the fuel nozzle 27 is provided.

(17) A burner seal 4 ensures the positioning of the fuel nozzle 27 in the head plate 5, and in particular in the supply opening 26 of the head plate 5. The burner seal 4, which may also be provided with cooling holes 16, is here mounted in floating fashion and, in the illustrated embodiment variant from the prior art, is positioned on the head plate 5 by means of a front positioning part in the form of a front positioning ring 24, and by means of a rear positioning part in the form of a rear positioning ring 28. Furthermore, the burner seal 4 is bolted to a heat shield 2 lying in the combustion space 23. For this, the heat shield 2 forms fixing elements in the form of bolts 17 which are guided through fixing openings on the head plate 5 and screwed on to the nuts 11 from the side of the combustion chamber head 3. Access for mounting the nuts 11 is provided via holes 19 in the combustion chamber head 3. According to the depiction in FIG. 6, the heat shield 2 may also have cooling air holes 14 and cooling ribs or studs. The bolts 17 may also be designed as separate components and need not be formed by the heat shield 2. Such bolts 17 are then for example screwed into threaded openings of the heat shield 2 from the side of the combustion chamber head 3.

(18) In order to achieve optimal conditions with regard to cooling and emission performance, in particular reliable positioning of the combustion chamber tile 6 relative to the mixing air holes 7 in the combustion chamber wall is necessary. It must furthermore be guaranteed that the mechanical integrity of the bolts 10 provided for fixing is not endangered by the positioning of the combustion chamber tile 6 relative to the combustion chamber wall 1a or 1b during installation and during operation of the engine T. In this context, it is usually disadvantageous for the positioning of a combustion chamber tile 6 relative to the combustion chamber wall 1a or 1b to be subject to relatively great spread, which must be taken into account in the design and tolerances to be expected. If a combustion chamber tile 6 is not positioned precisely with its mixing holes relative to the mixing air holes 7 in the combustion chamber wall, irregularities can occur in the temperature distribution of the process gas. This in turn has disadvantageous effects on the cooling air consumption and the fuel-air distribution in the combustion space 23.

(19) For a combustion chamber tile 6 as illustrated in FIGS. 1A and 1B, according to the proposed solution, a positioning aid with several positioning elements 61, 62 and 63 is integrated in the combustion chamber tile 6 in order to predefine a defined position relative to the combustion chamber wall 1a or 1b for the combustion chamber tile 6, and avoid the above-mentioned disadvantages.

(20) The combustion chamber tile 6 from FIGS. 1A and 1B has a rectangular base surface and thus has four mutually connected edges 6a to 6d. These edges 6a to 6d in particular edge a cold side 60 of the combustion chamber tile 6 facing the combustion chamber wall 1a or 1b in mounted state, on which several (screw or threaded) bolts 10.1-10.5 are formed. These bolts 10.1-10.5 pass through fixing openings 1.1-1.5 on the combustion chamber wall 1a or 1b so that the combustion chamber tile 6 can be fixed to the combustion chamber wall 1a or 1b via nuts 11 screwed onto the bolts 10.1-10.5.

(21) In the embodiment variant illustrated, several bolts 10.1, 10.2, and 10.4, 10.5 are provided close to the edge. A single bolt 10.3 is provided between two pairs of bolts 10.1/10.2 and 10.4/10.5 in a central region of the combustion chamber tile 6. This central bolt 10.3 is held concentrically in a fixing opening of the combustion chamber wall 1a or 1b with circular cross-section and also remains in position during operation of the engine T. In contrast, the bolts 10.1, 10.2, 10.4 and 10.5 arranged close to the edge, i.e. closer to the edges 6a, 6b, 6c and 6d, are received in the slot-like fixing openings 1.1, 1.2, 1.4 and 1.5 (shown exaggeratedly large in FIG. 1B) in order to allow or compensate for a thermally induced expansion of the combustion chamber tile 6 along a spatial axis y running axially.

(22) Because of the thermally induced expansion of the combustion chamber tile 6 in operation of the engine T, and the associated tolerances to be taken into account at the fixing openings 1.1-1.5 and at the mixing air holes 7.1 and 7.2 on the combustion chamber wall 1a or 1b which are assigned to a combustion chamber tile 6 and with which mixing air holes 67.1 and 67.2 of the combustion chamber tile 6 must be brought into alignment, previously conventional combustion chamber tiles 6 cannot easily be positioned precisely relative to a combustion chamber wall 1a or 1b. In order to remedy this problem, the positioning elements 61, 62 and 63 of the positioning aid integrated in the combustion chamber tile 6 are provided at an edge 671 or 672 of a mixing air hole 67.1 or 67.2 in the tile which protrudes in the form of a collar on the cold side 60 of the combustion chamber tile 6. The positioning elements 61, 62 and 63 are each formed as locally radially protruding lugs or webs and, when the combustion chamber tile 6 is attached to the combustion chamber wall 1a or 1b, bear against a contact face 710 or 720 formed by an inner casing surface of the respective assigned mixing air hole 7.1 or 7.2 in the combustion chamber.

(23) In the embodiment variant shown in FIGS. 1A and 1B, the mixing air holes 67.1 and 67.2 in the tile are arranged at different distances from the central bolt 10.3. At the mixing air hole 67.1 having the smallest distance from the central bolt 10.3, two positioning elements 61 and 62 are provided which protrude in two mutually perpendicular spatial directions y and x at the edge 671 of this mixing air hole 67.1. Via these positioning elements 61 and 63—relative to the fitted state—contact is possible in a direction along an axially running spatial axis y and also in a circumferential direction along a spatial axis x running perpendicularly thereto at the contact face 710 of the mixing air hole 7.1 in the combustion chamber wall. At the same time, an also radially locally protruding positioning element 62 is formed at the edge 672 of the other mixing air hole 67.2 in the tile, wherein with correct positioning of the combustion chamber tile 6 on the combustion chamber wall 1a or 1b, said positioning element also bears on the contact face 720 of the other mixing air hole 7.2 in the combustion chamber wall along the spatial axis y. Via the positioning elements 61, 62 and 63, for correct positioning of the combustion chamber tile 6 relative to the combustion chamber wall 1a or 1b, a defined contact is predefined in two spatial axes x and y, each running perpendicularly to an attachment direction +z in which the combustion chamber tile 6 is attached to an inside of the combustion chamber wall 1a or 1b.

(24) In the embodiment variant of FIGS. 1A and 1B, thus at the outer mixing air holes 7.1 and 7.2 in the tile, a positioning aid is constructed with positioning elements 61, 62 and 63 with dedicated contact faces for bearing on casing surfaces of mixing air holes 7.1 and 7.2 in the combustion chamber wall (in each case, at two mixing air holes 67.1 and 67.2 in the tile in the axial or longitudinal direction +y, and at only one mixing air hole 67.1 in the tile also in the circumferential direction +x). Thus a defined and reproducible positioning of the combustion chamber tile 6 relative to the combustion chamber wall 1a or 1b is achieved, while minimising the component tolerances to be taken into account on design, improving the inflow of air via the mixing air holes 7.1, 7.2, and hence avoiding the above-mentioned disadvantages. Also, the tolerance chain is minimised and the installation of the combustion chamber tile 6 on the combustion chamber wall 1a or 1b is considerably simplified, since there is no need for manual orientation of the combustion chamber tile 6. On installation of the combustion chamber tile 6 on the combustion chamber wall 1a or 1b, an engineer need merely ensure that the positioning elements 61, 62 and 63 bear against the contact faces 710, 720 in order to guarantee that the combustion chamber tile 6 is positioned correctly relative to the combustion chamber wall 1a or 1b, and in particular its mixing air holes 7.1 and 7.2, before then fixing the combustion chamber tile 6 via the bolts 10.1-10.5.

(25) The axial and circumferential positioning elements 61, 62 and 63 of the combustion chamber tile 6 in FIGS. 1A and 1B face the central bolt 10.3 in the broadest sense. The axial and circumferential positioning elements 61, 62 and 63 are thus provided on a portion of the protruding edge 671 or 672 of the mixing air holes 67.1 and 67.2 in the tile which does not face away from the central bolt 10.3. This furthermore prevents the positioning elements 61, 62 and 63 from being pressed against their contact faces 710 720 on the mixing air holes 7.1 and 7.2 in the combustion chamber wall because of the thermal expansion of the combustion chamber tile 6 in operation of the engine T (above all in the axial spatial axis y).

(26) In the embodiment variant of FIG. 2, for form-fit reception of axial (i.e. protruding along the y axis) positioning elements 61 and 62 of the combustion chamber tile 6, a respective positioning recess 1.61 or 1.62 is provided on the combustion chamber wall 1a or 1b in the region of the edge of the respective assigned mixing air hole 7.1 or 7.2 in the combustion chamber wall. Here, accordingly, the edge of a mixing air hole 7.1 or 7.2 in the combustion chamber wall comprises an additional radial cutout on the inside of the combustion chamber wall 1a or 1b. A locally protruding positioning element 61 or 62 of the combustion chamber tile 6 engages in this cutout when correctly attached to the combustion chamber walls 1a or 1b, and is brought into contact in the axial direction +y and/or in the circumferential direction +x in order to predefine the defined position of the combustion chamber tile 6 relative to the combustion chamber wall 1a or 1b.

(27) If merely a contact in the axial direction +y is provided at a contact face 161 or 162 of a positioning recess 1.61 or 1.62, then for contact in the circumferential direction +x, a positioning element 63 on the circumference may also be provided at a mixing air hole 7.1 in the tile, as shown in the embodiment variant of FIGS. 1A and 1B.

(28) In the embodiment variant of FIG. 3, no positioning elements 61, 62 or 63 are provided at the edges 671 and 672 of the mixing air holes 67.1 and 67.2 in the tile. Rather, the combustion chamber tile 6 here comprises on its cold side 60 two positioning elements which protrude separately in the direction of the combustion chamber wall 1a or 1b, in the form of first and second positioning pins 66a and 66b. These positioning pins 66a and 66b engage in positioning openings 1.66a and 1.66b formed on the inside of the combustion chamber wall 1a or 1b (not continuous openings), which form contact faces 166a and 166b for contact of the positioning pins 66a and 66b.

(29) A first positioning pin 66a, provided as an example close to the edge and centrally between two bolts 10.4 and 10.5, here engages concentrically in a positioning opening 1.66a of the combustion chamber wall 1a or 1b with circular cross-section. The second positioning pin 66b, spaced apart therefrom and arranged between bolts 10.1, 10.2 close to the edge and the central bolt 10.3, in contrast engages in a positioning opening 1.66b which has a slot-like cross-section. The second positioning pin 66b is here brought in the circumferential direction +x (or −x) into contact with one of two mutually opposing, primary contact face portions. The second positioning pin 66b is however spaced from the secondary contact face portions which connect together the two primary contact face portions and define the ends of the slot-like cross-section. With a positioning aid with such separate positioning elements 66a, 66b integrated on the cold side 60 of the combustion chamber tile 6, a positionally precise attachment of the combustion chamber tile 6 on the combustion chamber wall 1a or 1b is also achieved, and at the same time thermal expansion of the combustion chamber tile 6 in operation of the engine T can be taken into account.

(30) A combustion chamber tile 6 of the above-mentioned embodiment variants may in principle be produced by an additive production process or a casting process. It is provided for example that a combustion chamber tile 6 is first produced with the bolts 10.1-10.5 moulded thereon, and with the mixing air holes 67.1 and 67.2 in the tile. Then in a separate work process, for example the web-like positioning elements 61, 62 and 63 are moulded, which protrude at the edges 671 and 672 in spatial directions running perpendicularly to each other. In this way for example, a combustion chamber tile 6 may be produced conventionally for a combustion chamber portion BKA via an existing casting mould, and then the positioning elements 61, 62 and 63 of the positioning aid to be integrated in the combustion chamber tile 6 are moulded on.

LIST OF REFERENCE SIGNS

(31) 1.1-1.5 Bolt hole (fixing opening) 1.61, 1.62 Positioning recess 1.66a, 1.66b Positioning opening 10 Bolt (fixing element) 11 Nut 111 Low-pressure compressor 112 High-pressure compressor 113 High-pressure turbine 114 Medium-pressure turbine 115 Low-pressure turbine 12 Cooling hole 13 Effusion cooling hole 14 Cooling air hole 15 Cooling hole 16 Cooling hole 161, 162 Contact face 166a, 166b Contact face 17 Bolt (fixing element) 19 Hole 1a, 1b (Outer/inner) combustion chamber wall 2 Heat shield (tile component) 22 Outer casing 23 Combustion space 24 Front position ring 26 Passage hole (passage opening) 27 Fuel nozzle 28 Rear position ring 3 Combustion chamber head 4 Burner seal 5 Head plate (combustion chamber component) 6 Combustion chamber tile (tile component) 60 Cold side 61, 62 (Axial) positioning element 63 (Circumferential) positioning element 66a First positioning pin (positioning element) 66b Second positioning pin (positioning element) 67.1, 67.2 Mixing air hole in tile (passage opening) 671, 672 Edge 6a-6d Edge 7 Mixing air hole (supply opening) 7.1, 7.2 Mixing air hole in combustion chamber wall (supply opening) 710, 720 Contact face 8 Arm 9 Flange A Outlet B Bypass channel BK Combustion chamber BKA Combustion chamber portion C Outlet cone E Inlet/Intake F Fan F1, F2 Fluid flow FC Fan casing L Longitudinal axis M Central axis/axis of rotation S Rotor shaft T (Turbofan) engine TT Turbine V Compressor