TURBINE ENGINE COMBUSTION CHAMBER

Abstract

A turbine engine including a combustion chamber having an inner annular shroud and an outer annular shroud that are coaxial with each other and that are connected at their downstream ends respectively to an inner annular link wall and to an outer annular link wall, for linking respectively to an inner casing and to an outer casing. At least a first one of the inner and outer annular link walls includes at least one coolant fluid circuit extending between the radially inner and outer ends of said first annular link wall.

Claims

1. A turbine engine including a combustion chamber having an inner annular shroud and an outer annular shroud that are coaxial with each other and that are connected at their downstream ends respectively to an inner annular link wall and to an outer annular link wall, for linking respectively to an inner casing and to an outer casing, wherein at least a first one of the inner and outer annular link walls includes at least one coolant fluid circuit extending between the radially inner and outer ends of said first annular link wall.

2. A turbine engine according to claim 1, wherein said at least one circuit extends between air passage openings formed in said first link wall.

3. A turbine engine according to claim 2, wherein said first link wall includes a single coolant fluid circuit extending substantially through 360° and comprises a plurality of first portions extending radially between the openings in said first link wall.

4. A turbine engine according to claim 3, wherein each first portion has a U-shape formed by a bend portion connected to two branches that are substantially parallel to each other and are connected at their ends opposite from the bend portion to second portions extending substantially circumferentially.

5. A turbine engine according to claim 4, wherein all of the bend portions are arranged in the vicinity of the inner annular shroud or of the outer annular shroud to which the first link wall is connected.

6. A turbine engine according to claim 5, wherein the circuit includes a motor, e.g. an electric motor, suitable for causing the coolant fluid to flow in the circuit, and the circuit is connected to control means for controlling the speed of flow of the coolant fluid in the circuit.

7. A turbine engine according to claim 6, wherein the control means comprises a computer for controlling the speed of the motor, which computer is connected to a temperature sensor for sensing the temperature of the coolant fluid, and to a flowmeter.

8. A turbine engine according to claim 1, comprising a plurality of closed circuits that are mutually independent so that fluid cannot flow from one of them to another of them.

9. A turbine engine according to claim 8, wherein each closed circuit comprises two branches that extend substantially parallel to each other between the radially inner and outer ends of said first link wall.

10. A method of using the turbine machine according to claim 7, comprising actuating the fluid flow in the circuit of the first link wall when the flight phase corresponds to one of the phases comprising the takeoff phase and the cruising phase.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0024] The invention will be better understood other details, characteristics, and advantages of the invention appear on reading the following description given by way of non-limiting example and with reference to the accompanying drawings, in which:

[0025] FIG. 1 is a diagrammatic section view of a prior art combustion chamber, described above;

[0026] FIG. 2 is a diagrammatic view of a first embodiment of a fluid circuit formed in an outer link wall;

[0027] FIG. 3 is a diagrammatic view of a variant of the first embodiment of the invention; and

[0028] FIG. 4 is a diagrammatic view of a second embodiment comprising a plurality of fluid circuits formed in an outer link wall.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0029] Since FIG. 1 shows a combustion chamber of a known type that is described above, reference is made below to FIG. 2, which shows a first embodiment of the invention.

[0030] Unlike the prior art, the invention proposes to reduce the heat stresses in the inner and outer link walls 44, by incorporating at least one coolant fluid circuit 46 into them, the circuit 46 extending at least between the radially inner and outer ends of the wall 44 and being formed in its thickness.

[0031] The coolant fluid circuit is fluidically isolated from the air circulating around the combustion chamber through the orifices 40 of the inner and outer link walls.

[0032] In a first embodiment of the invention shown in FIG. 2, the outer link wall 44 includes a single coolant fluid circuit 46 extending through 360° about the axis of the turbine engine. The coolant fluid circuit 46 comprises a plurality of first portions 48 extending radially between the air passage openings 42 in the outer annular link wall 44. Each of these first portions 48 is U-shaped, made up of a bend portion 50 connected to two branches 52a, 52b that are substantially parallel to each other. The bend portions 50 are all arranged in the vicinity of the outer annular shroud 14 (see FIG. 1) and the ends of the branches 52a, 52b of each first portion 48 that are opposite from the bend portions 50 are connected to second circuit portions 54 that extend substantially circumferentially. Thus, each second circuit portion 54 extends circumferentially, radially outside relative to an opening 42 in the outer link wall 44.

[0033] In this embodiment, the fluid flowing, for example, as indicated by arrow A, is colder in the branch 52a than in the branch 52b.

[0034] In a variant of the FIG. 2 embodiment, it is possible to place the bend portions 50 in the vicinity of the outer casing 26, the ends of the branches 52a, 52b that are opposite from the bend portions then being connected to second portions 54 extending circumferentially in the vicinity of the outer annular shroud 14, radially inside relative to the opening 42.

[0035] In another variant, the outer link wall 56 may include a circuit 58 of a different shape. Thus, it is possible for each of the first portions 60a, 60b of the circuit 58 to be formed of a single branch (FIG. 3). Thus, each first portion 60a, 60b is connected at its radially inner end and at its radially outer end to a second portion 62 extending circumferentially, a second portion 62 being arranged radially inside relative to an opening 42 and a second portion 64 being arranged radially outside relative to an adjacent opening 42. In practice, the second portions 62, 64 are thus arranged annularly in staggered manner in succession and interconnected via the first portions 60a, 60b.

[0036] In this embodiment, the fluid flowing as indicated by arrow A, is colder in the branch 60a than in the branch 60b.

[0037] Each of the circuits 46, 58 of FIGS. 2 and 3 has a member for causing the coolant fluid to flow, it being possible for said member to be a motor, e.g. an electric motor. Advantageously, each circuit is connected to control means comprising a computer for controlling the speed of the motor, which computer is connected to a temperature sensor for sensing the temperature of the coolant fluid and to a flowmeter.

[0038] In operation, the coolant fluid flowing through the circuit 46, 58 makes it possible to transfer a fraction of the heat from the radially inner end of the outer link wall 44, 56 towards its radially outer end. It can thus be observed that the maximum amplitude of the temperature gradient is considerably smaller than in the prior art, thereby resulting in the local variations in temperature being smaller and making it possible to increase the lifespan of the link wall.

[0039] In a second embodiment of the invention, the outer link wall 62 may include a plurality of closed coolant fluid circuits 64, which circuits 64 are mutually independent so that fluid cannot flow from one of them to another of them. As shown in FIG. 4, each circuit 64 extends radially between two successive openings 42 in the outer link wall 62. Each circuit 64 comprises two branches 66 that are substantially parallel to each other and that are interconnected at their radially inner ends and at their radially outer ends. In this embodiment, the fluid flow in each circuit 64 takes place via vibration while the turbine engine is operating. In the same way as in the preceding embodiment, the reduction in the amplitude of the temperature gradient leads to an improvement in the mechanical strength, over time, of the outer link wall 62.

[0040] Although the invention is described above with reference to an outer link wall 44, 56, 62, it can be understood that it is also possible, without going beyond the ambit of the invention, to form one or more fluid circuits as described with reference to FIGS. 2, 3, and 4, in an inner link wall.

[0041] The coolant fluid should preferably be non-inflammable and be a good heat carrier. It is therefore possible to choose water as the coolant fluid. In the event of leakage of the coolant fluid from the fluid circuit, water flowing through the combustion chamber then corresponds to a situation of water being ingested by the turbine engine, the turbine engine being designed to cope with such a contingency.

[0042] In the configurations shown in FIGS. 2 and 3, it is desirable for the fluid to be caused to flow in the circuit 46, 58 only during flight phases such as take-off and cruising that correspond to phases during which the inner and outer link walls are subjected to the highest heat stresses. Conversely, during the less critical flight phases, such as descent, slowing down on the ground, or landing, the fluid flow in the circuit may be stopped.