Gas turbine engine, combustion chamber and manifold assembly thereof

Abstract

The invention aims to provide a gas turbine engine, a combustion chamber and a manifold assembly of the combustion chamber. The manifold assembly comprises a connecting opening, a closing-up part, a sealing ring, a blocking part and an elastic washer. A shoulder portion is formed between the closing-up portion and the connecting port, a sealing ring is arranged on the shoulder portion, a blocking portion is arranged on the inner side of an outlet of the connecting port, and an elastic washer is arranged between the blocking portion and the sealing ring. Wherein the sealing ring can elastically deform in the radial direction of the connecting opening, the elastic gasket can elastically deform under the action of external force, so that the sealing ring is allowed to have a certain displacement in the axial direction of the connecting opening, and the sealing performance of the cooling air active control system in the combustion chamber can be guaranteed through the manifold assembly.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbine engines, and in particular to a gas turbine engine, a combustion chamber and a manifold assembly thereof. Background Art

[0002] At present, the fuel consumption rate of aircraft engines, especially large bypass ratio civil aircraft engines, is an important indicator for their competition in the future international market. Based on the working principle of aircraft engines, the high-pressure gas compressed by the high-pressure compressor is fully mixed with the aviation kerosene flowing into the combustion chamber from the fuel adapter, and then ignited by the ignition nozzle, which burns violently and forms high-temperature and high-pressure combustion gas, which then expands and works through the turbine blades, and then drives the compressor to work through the connecting shaft, so as to realize the operation of the entire aircraft engine. In this process, the combustion chamber and the hot end components of the high-pressure turbine are subjected to high-temperature and high-pressure combustion gas, which brings great challenges to materials and cooling. Therefore, in order to meet the various working conditions of the normal operation of the engine in the overall structural design, it is necessary to carry out the design according to the worst working conditions, especially the cooling design for the hot end components is particularly important, that is, in the high-temperature takeoff state, the amount of cooling air used for the high-pressure turbine blade body needs to meet the cooling design requirements. However, in the state of low heat load of the turbine blades such as cruising, there is no need for cooling air equivalent to the amount of cooling air for high-temperature takeoff, so a means of regulation is required, that is, an active cooling air control system.

[0003] By adopting an active cooling air control system, the cooling air volume of the hot end components under various working conditions can be effectively adjusted to reduce engine fuel consumption. Since the device is a regulating device, it is directly connected to the inside of the hot end component through an external connection, which requires it to have good sealing properties. How to ensure the sealing properties of the active cooling air control system is a problem that needs to be solved urgently. Summary of the invention

[0004] The object of the present invention is to provide a manifold assembly capable of ensuring the sealing of an active control system for cooling air in a combustion chamber.

[0005] A manifold assembly for achieving the above-mentioned purpose is used in a combustion chamber and comprises:

[0006] a connection port, through which the cooling air active control system is connected to the combustion chamber;

[0007] A closing portion, wherein the inner diameter of the manifold assembly is contracted inwardly at the closing portion to form a shoulder between the closing portion and the connecting port;

[0008] A sealing ring, arranged on the shoulder, wherein the inner diameter of the sealing ring is smaller than the inner diameter of the closing portion;

[0009] a blocking portion, arranged at the inner side of the outlet of the connecting port; and

[0010] An elastic gasket, disposed between the stopper and the sealing ring;

[0011] The sealing ring is elastically deformable along the radial direction of the connection port, and the elastic gasket is elastically deformable under the action of an external force, so as to allow the sealing ring to have a certain displacement along the axial direction of the connection port.

[0012] In one or more embodiments, annular washers are further provided on both sides of the elastic washer along the axial direction of the connecting port.

[0013] In one or more embodiments, the elastic gasket is in the shape of a corrugated ring.

[0014] In one or more embodiments, a clamping groove is provided inside the outlet of the connection port, a clamping ring is provided inside the clamping groove, and the clamping ring forms the blocking portion.

[0015] In one or more embodiments, the collar has an opening, and the outer diameter of the collar can be changed by applying force at the opening.

[0016] In one or more embodiments, the sealing ring is hollow and has an opening on the radial outer side, and the opening allows the sealing ring to be elastically deformed under the application of external force so that the inner diameter of the sealing ring is changed.

[0017] On the other hand, according to some embodiments of the present application, there is also provided a combustion chamber, which includes a cooling air active control and regulation system, a combustion chamber outer casing, and a manifold assembly as described above;

[0018] The cooling air active control and adjustment system extends from the outside into the combustion chamber casing and then into the manifold assembly, and the sealing ring seals the connection between the cooling air active control and adjustment and the manifold assembly.

[0019] In one or more embodiments, the inner periphery of the sealing ring is in line contact and seal with the outer tube wall of the cooling air active control and regulation system, and the sealing ring is elastically supported by the elastic gasket so that the end face of the sealing ring is in line contact and seal with the shoulder.

[0020] In one or more embodiments, the smallest inner diameter of the inner ring of the sealing ring is 1 mm to 2 mm smaller than the outer diameter of the outer tube of the active air control and regulation system.

[0021] On the other hand, according to some embodiments of the present application, a gas turbine engine is provided, comprising the combustion chamber as described above.

[0022] The beneficial effects of the present invention are:

[0023] The manifold assembly has an axial floating structure, and two layers of annular gaskets are fixed in the manifold assembly by a clamp ring. An elastic gasket with an elastic structure is placed between the two annular gaskets, wherein the structural dimensions of the elastic gasket are controlled to achieve the deformation amount of the elastic gasket between the two layers of annular gaskets, so that the air active control and adjustment system can penetrate into the pipeline through this position. Due to the axial activity provided by its elastic gasket, it can adapt to the axial deformation amount under different working conditions of the engine, and avoid damage caused by the connection between the cooling air control and adjustment mechanism and the pipeline being stuck. The manifold assembly has a simple configuration structure and is easy to disassemble and assemble. Since it can be replaced in time only through ordinary gaskets, clamp rings, elastic gaskets and lip sealing ring structures, it has the advantages of rapid detection and convenient maintenance.

[0024] The above description is only an overview of the technical solution of the present application. In order to more clearly understand the technical means of the present application, it can be implemented in accordance with the contents of the specification. In order to make the above and other purposes, features and advantages of the present application more obvious and easy to understand, the specific implementation methods of the present application are listed below. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Various other advantages and benefits will become apparent to those of ordinary skill in the art by reading the detailed description of the preferred embodiments below. The accompanying drawings are only for the purpose of illustrating the preferred embodiments and are not to be considered as limiting the present application. Moreover, the same reference numerals are used throughout the drawings to represent the same components. In the drawings:

[0026] Figure 1 A schematic diagram of an embodiment of the combustion chamber is shown;

[0027] Figure 2 A half-section schematic diagram of some embodiments of the manifold assembly is shown;

[0028] Figure 3 A partial enlarged schematic diagram of a connection port of the manifold assembly according to the present invention is shown;

[0029] Figure 4 Shows a three-dimensional schematic diagram of some embodiments of the clamp ring;

[0030] Figure 5 Shown are three-dimensional schematic diagrams of some embodiments of the sealing ring. DETAILED DESCRIPTION

[0031] The following embodiments of the technical solution of the present application are described in detail in conjunction with the accompanying drawings. The following embodiments are only used to more clearly illustrate the technical solution of the present application, and are therefore only used as examples, and cannot be used to limit the scope of protection of the present application.

[0032] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by technicians in the technical field to which this application belongs; the terms used herein are only for the purpose of describing specific embodiments and are not intended to limit this application; the terms "including" and "having" in the specification and claims of this application and the above-mentioned figure descriptions and any variations thereof are intended to cover non-exclusive inclusions.

[0033] Modulated Tubine Cooling (MTC) is an active cooling air control system that actively adjusts the amount of cooling air for the high-pressure turbine according to the different operating conditions of the engine. When the heat load of the high-pressure turbine is large (such as takeoff), sufficient cooling air is provided to it through MTC. When the heat load of the high-pressure turbine is small (such as cruising), the supply of cooling air is appropriately reduced, thereby reducing the fuel consumption rate of the engine.

[0034] In order to achieve effective sealing of the active control system of cooling air in the combustion chamber, on the one hand, according to some embodiments of the present application, a combustion chamber is provided, such as Figure 1 FIG. 1 shows a schematic diagram of an embodiment of the combustion chamber. It can be understood that: Figure 1 The diagram shown is only for the purpose of showing the structural connection relationship between the main components in the combustion chamber. In fact, the combustion chamber can have more structural details. The combustion chamber includes a cooling air active control and adjustment system 91, a combustion chamber outer casing 92 and a manifold assembly 100. Specifically, among the components shown in the figure, the combustion chamber also includes a pre-diffuser 93, a flame tube 95, a pre-swirl nozzle 96 and other bolts and other structures. The cooling air active control and adjustment device 91 directly penetrates into the combustion chamber outer casing 92 from the outside, and then the entire device penetrates into the manifold structure 100, and is sealed by the sealing structure of the manifold structure 100. At the same time, the manifold structure 100 is directly fixed to the rear flange of the pre-diffuser 93 by bolts, and then the pipeline passes through the flame tube 95 and the inner annular cavity channel of the inner casing and extends into the pre-swirl nozzle 96, so that the air bleed function can be achieved.

[0035] On the other hand, according to some embodiments of the present application, a manifold assembly 100 is further provided. The manifold assembly 100 can be applied to the combustion chamber described in the above-mentioned embodiments. Figure 2 A half-section schematic diagram of some embodiments of the manifold assembly is shown. The manifold assembly 100 includes a connection port 1, a closing portion 2, a sealing ring 3, a stopper 4, and an elastic gasket 5. Figure 3The diagram shows a partial enlarged schematic diagram of the connection port of the manifold assembly according to the present invention. The cooling air active control system 91 is connected to the combustion chamber through the connection port 1 of the manifold assembly 100. The inner diameter of the manifold assembly 100 is retracted at the closing portion 2 to form a shoulder 20 between the closing portion 2 and the connection port 1. The sealing ring 3 is arranged at the shoulder 20, and the inner diameter of the sealing ring 3 is smaller than the inner diameter of the closing portion 2. The stopper 4 is arranged at the inner side of the outlet of the connection port 1, and the elastic gasket 5 is arranged between the stopper 4 and the sealing ring 3.

[0036] The sealing ring 3 can be elastically deformed along the radial direction a of the connecting port 1 , and the elastic gasket 5 can be elastically deformed under the action of external force to allow the sealing ring 3 to have a certain displacement along the axial direction b of the connecting port 1 .

[0037] In the assembled state, the cooling air active control and regulation system 91 extends from the outside into the combustion chamber 92, and then extends into the manifold assembly 100, and the sealing ring 3 seals the connection between the cooling air active control and regulation system 91 and the manifold assembly 100. The cooling air is directly supplied to the pre-swirl nozzle through the cooling air active control and regulation system 91 pipeline to supply high vortex cooling. During the process, the outer wall of the cooling air active control and regulation system 91 pipeline and the manifold assembly 100 have different overall temperature fields due to their different fixed positions. At the same time, due to direct contact, there are thermal deformation incoordination and leakage risks. The patent design configures the sealing ring 3 to be elastically deformable along the radial direction a of the connection port 1 and has a certain displacement space along the axial direction b of the connection port 1 to adapt to the axial floating amount caused by the incoordination of deformation under different working conditions, and to achieve sealing of the connection, which can ensure the airtightness of the cooling air active control device and avoid the influence of insufficient gas supply caused by leakage during the working process.

[0038] In the description of the embodiments of the present application, the technical terms "first", "second", etc. are only used to distinguish different objects, and cannot be understood as indicating or implying relative importance or implicitly indicating the number, specific order or primary and secondary relationship of the indicated technical features. In the description of the embodiments of the present application, the meaning of "multiple" is more than two, unless otherwise clearly and specifically defined.

[0039] Reference to "embodiments" herein means that a particular feature, structure, or characteristic described in conjunction with the embodiments may be included in at least one embodiment of the present application. The appearance of the phrase in various locations in the specification does not necessarily refer to the same embodiment, nor is it an independent or alternative embodiment that is mutually exclusive with other embodiments. It is explicitly and implicitly understood by those skilled in the art that the embodiments described herein may be combined with other embodiments.

[0040] In some embodiments of the manifold assembly, annular gaskets 6 are provided on both sides of the elastic gasket 5 along the axial direction b of the connecting port 1, so that the elastic gasket 5 can be applied with force on both sides through the annular gaskets 6, thereby ensuring the stability of the fixing of the elastic gasket 5 and preventing dislocation and the like from occurring.

[0041] In some embodiments of the manifold assembly, the elastic gasket 5 is in a corrugated ring shape. Specifically, the elastic gasket 5 has a geometric center, and the minimum distance from the geometric center to the outer edge of the elastic gasket 5 is the outer diameter of the elastic gasket 5. A reference circle is formed with the geometric center as the center and the outer diameter of the elastic gasket 5 as the radius. The elastic gasket 5 has at least one convex section that is convex relative to the plane where the reference circle is located and at least one concave section that is concave relative to the plane where the reference circle is located. The convex section and the concave section form an elastic gasket 5 in a corrugated ring shape, and the distance between the convex section and the concave section relative to the plane where the reference circle is located defines the elastic deformation amount of the elastic gasket 5. The elastic gasket 5 with this configuration is easy to assemble and fix, and the elastic deformation amount of the elastic gasket 5 can be adjusted by adjusting the distance between the convex section and the concave section relative to the plane where the reference circle is located, so as to determine the displacement amount of the sealing ring 3 along the axial direction b of the connecting port 1.

[0042] In some embodiments of the manifold assembly, a clamping groove 10 is provided inside the outlet of the connection port 1, and a clamping ring is provided inside the clamping groove, and the clamping ring forms a stopper 4. In this way, the clamping ring can be assembled to form a component for limiting the outlet of the connection port 1, and the clamping ring can be replaced when it is worn to increase the service life of the manifold assembly. In other embodiments different from those shown in the figure, the stopper 4 can also be a convex ring protruding toward the inside of the outlet of the connection port 1.

[0043] Figure 4 A stereoscopic schematic diagram of some embodiments of the clamp ring is shown. The clamp ring 4 has an opening 40 . The outer diameter of the clamp ring 4 can be changed by applying force at the opening 40 , thereby facilitating the assembly of the clamp ring 4 in the clamping groove 10 .

[0044] Figure 5 A three-dimensional schematic diagram of some embodiments of the sealing ring is shown, wherein the sealing ring 3 is hollow and has a sealing ring upper end 30, a sealing ring lower end 31 and a sealing ring inner edge 32, and an opening 33 is provided at the outer edge of the sealing ring radially outside between the sealing ring upper end 30 and the sealing ring lower end 31. When force is applied to the sealing ring upper end 30 and the sealing ring lower end 31, the size of the opening 33 can change, so that the sealing ring 3 is elastically deformed to allow the inner diameter of the sealing ring defined at the sealing ring inner edge 32 to be changed.

[0045] In some embodiments of the combustion chamber, in the assembled state, the inner periphery of the sealing ring 3 is in line contact and seal with the outer tube wall of the cooling air active control and regulation system 91, and the sealing ring 3 is elastically supported by the elastic gasket 5, so that the end face of the sealing ring 3, that is, the end face of the lower end 31 of the sealing ring is in line contact and seal with the shoulder 20, thereby ensuring the reliability of the sealing effect.

[0046] In some embodiments of the present combustion chamber, the smallest inner diameter of the inner ring of the sealing ring 3 is 1 mm to 2 mm smaller than the outer diameter of the outer tube of the active air control and regulation system 91, so as to ensure that when the air duct of the active air control and regulation system 91 passes through the sealing ring 3, the sealing ring 3 structure can be squeezed so that the inner wall surface is forced to expand outward. At the same time, since the sealing ring 3 is assembled on the lower side of the double-layer annular gasket 6 and the elastic gasket 5, it is also subjected to the elastic force of the elastic gasket 5 between the double-layer annular gasket 6, so as to ensure that it is radially stressed and limit its radial displacement. Through the influence of the above two stresses, the end face of the upper end 30 of the sealing ring and the lower end face of the double-layer annular gasket 6 are linearly sealed, and the inner edge 32 of the sealing ring and the outer tube wall of the active air control and regulation system 91 are linearly sealed. Moreover, under the action of this force, the end face of the lower end 31 of the sealing ring is tightly fitted with the shoulder 20 to achieve linear sealing. Under the normal working state of the engine, the sealing structure can ensure the air tightness of the active cooling air control device and avoid the influence of insufficient gas supply caused by leakage during operation.

[0047] On the other hand, according to some embodiments of the present application, a gas turbine engine is provided, comprising the combustion chamber as described above.

[0048] The manifold assembly has an axial floating structure, and two layers of annular gaskets 6 are fixed in the manifold assembly by a clamp ring 4, and an elastic gasket 5 with an elastic structure is placed between the two annular gaskets 6, wherein the structural dimensions of the elastic gasket 5 are controlled to achieve the deformation amount of the elastic gasket 5 between the two layers of annular gaskets 6, so as to realize that after the air active control and adjustment system 91 passes through this position and penetrates into the pipeline, due to the axial activity provided by its elastic gasket 5, it can adapt to the axial deformation amount under different working conditions of the engine, and avoid the cooling air control and adjustment mechanism and the pipeline connection from being stuck and causing damage. The manifold assembly has a simple configuration structure and is easy to disassemble and assemble. Since it can be replaced in time only through ordinary gaskets, clamp rings, elastic gaskets and lip sealing ring structures, it has the advantages of rapid detection and convenient maintenance.

[0049] In the description of the embodiments of the present application, unless otherwise clearly specified and limited, technical terms such as "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, and it can be the internal connection of two elements or the interaction relationship between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the embodiments of the present application can be understood according to the specific circumstances.

[0050] It should be understood that "along" a certain direction mentioned in the text means that there is at least a component in the direction, preferably, the angle with the direction is within 10°, and more preferably, the angle is within 5°.

[0051] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit them; although the present application has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein by equivalents; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the embodiments of the present application, and they should all be included in the scope of the claims and specification of the present application. In particular, as long as there is no structural conflict, the various technical features mentioned in the various embodiments can be combined in any way. The present application is not limited to the specific embodiments disclosed herein, but includes all technical solutions that fall within the scope of the claims.

Claims

1. A manifold assembly for a combustion chamber, characterized in that: include: a connection port, through which the cooling air active control system is connected to the combustion chamber; A closing portion, wherein the inner diameter of the manifold assembly is contracted inwardly at the closing portion to form a shoulder between the closing portion and the connecting port; A sealing ring, arranged on the shoulder, wherein the inner diameter of the sealing ring is smaller than the inner diameter of the closing portion; a blocking portion, arranged at the inner side of the outlet of the connecting port; and An elastic gasket, disposed between the stopper and the sealing ring; The sealing ring is elastically deformable along the radial direction of the connection port, and the elastic gasket is elastically deformable under the action of an external force, so as to allow the sealing ring to have a certain displacement along the axial direction of the connection port.

2. The manifold assembly of claim 1, wherein: Annular washers are also arranged on both sides of the elastic washer along the axial direction of the connecting port.

3. The manifold assembly of claim 1, wherein: The elastic gasket is in a corrugated ring shape.

4. The manifold assembly of claim 1, wherein: A clamping groove is arranged inside the outlet of the connection port, a clamping ring is arranged inside the clamping groove, and the clamping ring forms the blocking portion.

5. The manifold assembly of claim 4, wherein: The collar has an opening, and the outer diameter of the collar can be changed by applying force at the opening.

6. The manifold assembly of claim 1, wherein: The sealing ring is hollow and has an opening on the radial outer side. The opening allows the sealing ring to be elastically deformed under external force so that the inner diameter of the sealing ring is changed.

7. A combustion chamber, characterized in that: It comprises a cooling air active control and regulation system, a combustion chamber outer casing and a manifold assembly as claimed in any one of claims 1 to 6; The cooling air active control and adjustment system extends from the outside into the combustion chamber casing and then into the manifold assembly, and the sealing ring seals the connection between the cooling air active control and adjustment and the manifold assembly.

8. The combustion chamber according to claim 7, characterized in that The inner periphery of the sealing ring is in line contact and sealing with the outer tube wall of the cooling air active control and regulation system, and the sealing ring is elastically supported by the elastic gasket so that the end face of the sealing ring is in line contact and sealing with the shoulder.

9. The combustion chamber according to claim 8, characterized in that The smallest inner diameter of the inner ring of the sealing ring is 1 mm to 2 mm smaller than the outer diameter of the outer tube of the active air control and regulation system.

10. A gas turbine engine, characterized in that: Comprising a combustion chamber as claimed in any one of claims 7 to 9.

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