Gas turbine engine, combustion chamber and manifold assembly thereof

Abstract

The application aims to provide a gas turbine engine, a combustion chamber and a manifold assembly thereof. The manifold assembly comprises a connecting port, a closing-in portion, a sealing ring, a blocking portion and a resilient washer. A shoulder is formed between the closing-in portion and the connecting port, the sealing ring is arranged on the shoulder, the blocking portion is arranged inside the outlet of the connecting port, and the resilient washer is arranged between the blocking portion and the sealing ring. The sealing ring is elastically deformable along the radial direction of the connecting port, and the resilient washer is elastically deformable under external force, so as to allow the sealing ring to have a certain displacement amount along the axial direction of the connecting port. The sealing property of the active cooling air control system in the combustion chamber can be ensured by using the manifold assembly.

Description

TECHNICAL FIELD

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

[0002] Currently, the fuel consumption rate of an aero-engine, especially a large-bypass-ratio civil aero-engine, is an important indicator for its competition in the future international market. Based on the working principle of an aero-engine, high-pressure gas compressed by a high-pressure compressor is mixed with aviation kerosene flowing into a combustion chamber from a fuel adapter, ignited by an ignition electrode, and combusted violently to form high-temperature and high-pressure gas, so that the gas expands to do work through turbine blades, and then drives the compressor through a connecting shaft to work, thereby realizing the operation of the aero-engine. In this process, the combustion chamber and the high-temperature end components bear high-temperature and high-pressure gas, which brings great challenges to the material and cooling. Therefore, in the overall structural design, in order to meet the various working conditions of the engine, the design needs to be carried out according to the most severe working state, especially the cooling design of the hot end components, i.e., in the high-temperature take-off state, the cooling air quantity for the high-pressure turbine blade needs to meet the cooling design requirements. However, in the turbine blade small heat load state such as cruising, the cooling air quantity does not need to be equivalent to that in the high-temperature take-off state, so a regulating means, i.e., a cooling air active control system, is needed.

[0003] By adopting the cooling air active control system, the cooling air quantity of the hot end components in various working states can be effectively adjusted, and the fuel consumption of the engine is reduced. Since the device is a regulating device, it is directly connected to the inside of the hot end component through external connection, which requires good sealing. How to ensure the sealing of the cooling air active control system is a problem that needs to be solved at present. SUMMARY

[0004] The purpose of the present application is to provide a manifold assembly that can ensure the sealing of the cooling air active control system in the combustion chamber.

[0005] To achieve the above-mentioned purpose, the manifold assembly for the combustion chamber comprises:

[0006] A connecting port through which the cooling air active control system is connected to the combustion chamber;

[0007] A necked portion, in which the inner diameter of the manifold assembly is reduced, so as to form a shoulder between the necked portion and the connecting port;

[0008] A sealing ring arranged at the shoulder, the inner diameter of the sealing ring being smaller than that of the necked portion;

[0009] A blocking portion arranged inside the outlet of the connecting port; and

[0010] an elastic washer arranged between the blocking part and the sealing ring;

[0011] wherein the sealing ring is elastically deformable along the radial direction of the connecting port, and the elastic washer is elastically deformable under external force to allow the sealing ring to have a certain displacement along the axial direction of the connecting port.

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

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

[0014] In one or more embodiments, a clamping groove is arranged inside the outlet of the connecting port, and a clamping ring is arranged in the clamping groove, the clamping ring forming the blocking part.

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

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

[0017] In another aspect, the application also provides a combustor comprising a cooling air active control adjustment system, a combustor outer casing, and a manifold assembly as described above.

[0018] wherein the cooling air active control adjustment system extends into the manifold assembly after extending into the combustor outer casing, and the sealing ring seals the connection between the cooling air active control adjustment system and the manifold assembly.

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

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

[0021] In yet another aspect, the application also provides a gas turbine engine comprising a combustor as described above.

[0022] The application has the following advantages:

[0023] The manifold assembly has an axial floating structure, two annular gaskets are fixed in the manifold assembly through the ring, and the elastic gasket with elastic structure is placed between the two annular gaskets, wherein the structure size of the elastic gasket is controlled to realize the deformation amount of the elastic gasket between the double-layer annular gasket, so that the air active control adjustment system can adapt to the axial deformation amount under different working conditions of the engine after penetrating into the pipeline through the position, and the damage caused by the clamping of the cooling air control adjustment mechanism and the pipeline is avoided. The manifold assembly has simple structure and convenient disassembly and assembly, and can be replaced in time through the structure of ordinary gasket, ring, elastic gasket and lip seal ring, and has the advantages of rapid detection and convenient maintenance.

[0024] The above description is only a summary of the technical scheme of the present application, in order to more clearly understand the technical means of the present application, and can be implemented according to the content of the specification, and in order to make the above and other purposes, characteristics and advantages of the present application more obvious and easy to understand, the following specific embodiments of the present application are described. BRIEF DESCRIPTION OF DRAWINGS

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

[0026] Figure 1 A schematic diagram according to one embodiment of the present combustion chamber is shown;

[0027] Figure 2 A semi-sectional schematic diagram according to some embodiments of the present manifold assembly is shown;

[0028] Figure 3 A local enlarged schematic diagram of the connecting port according to the present manifold assembly is shown;

[0029] Figure 4 A three-dimensional schematic diagram according to some embodiments of the present ring is shown;

[0030] Figure 5 A three-dimensional schematic diagram according to some embodiments of the present sealing ring is shown. DETAILED DESCRIPTION

[0031] The embodiments of the technical scheme of the present application will be described in detail below with reference to the drawings. The following embodiments are only used to more clearly illustrate the technical scheme of the present application, therefore only as an example, and cannot limit the protection scope of the present application.

[0032] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs; the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of this application; the use of the terms "including," "comprising," or "having" and variations thereof herein is intended to be broad and encompass the terms "consisting of" and "consisting essentially of" and variations thereof. Unless otherwise required by context, singular terms shall include pluralities and vice versa. Unless otherwise required by context, the use herein of the singular is also to be construed as coverage of the plural and vice versa.

[0033] Modulated Tubine Cooling (MTC): refers to the cooling air quantity of the high-pressure turbine being actively adjusted according to the working state of the engine; when the thermal load of the high-pressure turbine is large (such as during takeoff), the MTC provides sufficient cooling air to the high-pressure turbine; when the thermal load of the high-pressure turbine is small (such as during cruising), the supply of cooling air is appropriately reduced, thereby reducing the specific fuel consumption of the engine.

[0034] In order to realize effective sealing of the active cooling air control system 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 A schematic diagram according to an embodiment of the combustion chamber is shown, and 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, and in fact the combustion chamber can have more structural details. The combustion chamber includes a cooling air active control 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 further includes a front diffuser 93, a flame tube 95, a pre-swirl nozzle 96, and other bolt structures. The cooling air active control adjustment system 91 is directly inserted into the interior of the combustion chamber outer casing 92 from the outside, and then the entire device is inserted into the interior of the manifold structure 100, and sealing is achieved through the sealing structure of the manifold structure 100. At the same time, the manifold structure 100 is directly fixed on the rear flange of the front diffuser 93 through bolts, and then the pipeline is passed through the flame tube 95 and the inner ring cavity passage of the inner casing, and is inserted into the pre-swirl nozzle 96, thereby realizing the bleed air function.

[0035] On the other hand, according to some embodiments of the present application, a manifold assembly 100 is also provided, which can be applied to the combustion chamber as described in the embodiments described above, Figure 2 A semi-partial schematic diagram according to some embodiments of the manifold assembly is shown, and the manifold assembly 100 includes a connecting port 1, a closing port portion 2, a sealing ring 3, a blocking portion 4, and an elastic gasket 5, Figure 3As shown in the partial enlarged view of the connecting port of the manifold assembly according to the present application, the cooling air active control system 91 is connected with the combustion chamber through the connecting port 1 of the manifold assembly 100, the inner diameter of the manifold assembly 100 is reduced in the necked portion 2 to form a shoulder 20 between the necked portion 2 and the connecting port 1, a sealing ring 3 is arranged on the shoulder 20, and the inner diameter of the sealing ring 3 is smaller than that of the necked portion 2. A blocking portion 4 is arranged inside the outlet of the connecting port 1, and an elastic gasket 5 is arranged between the blocking portion 4 and the sealing ring 3.

[0036] In the present application, the sealing ring 3 is elastically deformable along the radial direction a of the connecting port 1, and the elastic gasket 5 is elastically deformable under the action of an external force to allow the sealing ring 3 to have a certain displacement amount along the axial direction b of the connecting port 1.

[0037] In the assembled state, after the cooling air active control system 91 extends into the outer casing 92 of the combustion chamber from the outside, the sealing ring 3 seals the connection between the cooling air active control system 91 and the manifold assembly 100. The cooling air is directly supplied to the pre-swirl nozzle through the pipeline of the cooling air active control system 91 for high-vortex cooling, and in the process, the temperature field of the whole is different due to the different fixed positions between the outer wall surface of the pipeline of the cooling air active control system 91 and the manifold assembly 100, and there is a risk of thermal deformation incoordination and leakage due to direct contact. In the present application, the sealing ring 3 is configured to be elastically deformable along the radial direction a of the connecting port 1 and to have a certain displacement space along the axial direction b of the connecting port 1 to adapt to the axial floating amount caused by deformation incoordination in different working states, and to seal the connection, so as to ensure the air tightness of the cooling air active control device and avoid the influence caused by insufficient air supply due to air leakage during work.

[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 "a plurality of" is two or more, unless otherwise explicitly and specifically limited.

[0039] In this document, the term "embodiment" means that the specific features, structures or characteristics described in connection with the embodiment can be included in at least one embodiment of the present application. The appearance of this phrase in various places in the specification does not necessarily mean the same embodiment, nor is it independent or alternative to other embodiments. It is explicitly and implicitly understood by those skilled in the art that the embodiments described herein can 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 pressed by the annular gaskets 6 on both sides, thereby ensuring the stability of the elastic gasket 5 and preventing dislocation and other phenomena.

[0041] In some embodiments of the manifold assembly, the elastic gasket 5 is in the form of a corrugated ring. 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 protruding above the plane of the reference circle and at least one concave section below the plane of the reference circle, and the convex section and the concave section form the corrugated ring-shaped elastic gasket 5. The distance of the convex section and the concave section relative to the plane of the reference circle 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 of the convex section and the concave section relative to the plane of the reference circle, 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 connecting port 1, and a clamping ring is arranged in the clamping groove to form the stop portion 4. In this way, the clamping ring can be assembled to limit the components at the outlet of the connecting port 1, and the clamping ring can be replaced when it is worn out, thereby improving the service life of the manifold assembly. In other embodiments different from those shown in the drawings, the stop portion 4 can also be a protruding ring arranged towards the inside of the outlet of the connecting port 1.

[0043] Figure 4 A three-dimensional schematic view according to some embodiments of the clamping ring is shown. The clamping ring 4 has an opening 40, and the size of the outer diameter of the clamping ring 4 can be changed by applying force at the opening 40, thereby facilitating the assembly of the clamping ring 4 in the clamping groove 10.

[0044] Figure 5 A three-dimensional schematic view according to some embodiments of the sealing ring is shown. The sealing ring 3 is in the form of a hollow ring, 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 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 by 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 linear contact with the outer pipe wall of the cooling air actively controlled adjustment system 91, and the sealing ring 3 is elastically supported by the elastic washer 5, so that the end surface of the sealing ring 3, i.e. the end surface of the lower end 31 of the sealing ring, is in linear contact with the shoulder 20, thereby ensuring the reliability of the sealing effect.

[0046] In some embodiments of the combustion chamber, the inner diameter of the inner ring of the sealing ring 3 is smaller than the outer diameter of the outer pipe of the air actively controlled adjustment system 91 by 1-2 mm, so that when the air actively controlled adjustment system 91 passes through the sealing ring 3, the structure of the sealing ring 3 can be squeezed, so that the inner side wall surface is forced to expand outward, and at the same time, the sealing ring 3 is assembled below the double-layer annular washer 6 and the elastic washer 5, and is also subjected to the elastic force of the elastic washer 5 between the double-layer annular washer 6, thereby ensuring the radial force and limiting the radial displacement amount. Through the above two stress effects, the end surface of the upper end 30 of the sealing ring is in linear contact with the lower end surface of the double-layer annular washer 6, and the inner edge 32 of the sealing ring is in linear contact with the outer pipe wall of the air actively controlled adjustment system 91, and the end surface of the lower end 31 of the sealing ring is tightly attached to the shoulder 20 under the action of the force, thereby realizing linear sealing. In the normal working state of the engine, the sealing structure can ensure the air tightness of the cooling air actively controlled device, and avoid the influence caused by insufficient air supply due to air leakage during work.

[0047] In another aspect, according to some embodiments of the present application, a gas turbine engine is also provided, which comprises the combustion chamber as described above.

[0048] The manifold assembly has an axial floating structure, the two-layer annular washers 6 are fixed in the manifold assembly by the clamping ring 4, and the elastic washer 5 with elastic structure is placed between the two annular washers 6, wherein the structure size of the elastic washer 5 is controlled to realize the deformation amount of the elastic washer 5 between the double-layer annular washers 6, so that after the air actively controlled adjustment system 91 passes through this position and penetrates into the pipeline, the axial movement amount provided by the elastic washer 5 can adapt to the axial deformation amount under different working conditions of the engine, thereby avoiding damage caused by the jamming of the cooling air control adjustment mechanism and the pipeline connection. The manifold assembly has simple structure and is convenient to disassemble and assemble, and can be replaced in time by only using the structure of ordinary gasket, clamping ring, elastic washer and lip seal ring, thereby having the advantages of quick detection and convenient maintenance.

[0049] In the description of the embodiments of the present application, unless specifically defined and limited otherwise, the terms "mounting", "connected", "connection", "fixed", and the like should be understood broadly, for example, can be fixed connection, can also be detachable connection, or integral; can be mechanical connection, can also be electrical connection; can be direct connection, can also be indirect connection through an intermediate medium, can be internal communication of two elements or interaction relationship between two elements. For those skilled 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 the "along" a direction mentioned in the text means that there is at least a component in the direction, preferably the included angle with the direction is within 10°, more preferably the included 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, and not to limit them; although the present application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that: it can still modify the technical solutions recorded in the foregoing embodiments, or make equivalent replacement for part or all of the technical features; 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 be covered in the scope of the claims and the description of the present application. Especially, as long as there is no structural conflict, each technical feature mentioned in each embodiment can be combined in any way. The present application is not limited to the specific embodiments disclosed herein, but includes all technical solutions falling within the scope of the claims.

Claims

1. A manifold assembly for a combustion chamber, characterized by, The manifold assembly comprises: a connecting port through which the cooling air active control system is connected to the combustion chamber; a necked portion, in which the inner diameter of the manifold assembly is reduced to form a shoulder between the necked portion and the connecting port; a sealing ring arranged at the shoulder, the inner diameter of the sealing ring being smaller than that of the necked portion; a stop arranged inside the outlet of the connecting port; and a resilient washer arranged between the stop and the sealing ring; wherein the sealing ring is elastically deformable in the radial direction of the connecting port, and the resilient washer is elastically deformable under external force to allow the sealing ring to have a certain displacement in the axial direction of the connecting port; annular washers are further arranged on both sides of the resilient washer in the axial direction of the connecting port; a clamping groove is arranged inside the outlet of the connecting port, and a clamping ring is arranged in the clamping groove, the clamping ring forming the stop.

2. The manifold assembly of claim 1, wherein, The resilient washer is in the form of a corrugated ring.

3. The manifold assembly of claim 1, wherein, The clamping ring has an opening, and the outer diameter of the clamping ring can be changed by applying force at the opening.

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

5. A combustion chamber, characterized by The cooling air active control system, the combustion chamber outer casing, and the manifold assembly according to any one of claims 1 to 4 are provided. After the cooling air active control system extends into the combustion chamber outer casing from the outside, it extends into the manifold assembly, and the sealing ring seals the connection between the cooling air active control system and the manifold assembly.

6. The combustion chamber of claim 5, wherein The inner periphery of the sealing ring is in linear contact with the outer tube wall of the cooling air active control system, and the sealing ring is elastically supported by the resilient washer, so that the end surface of the sealing ring is in linear contact with the shoulder.

7. The combustion chamber of claim 6, wherein The minimum 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 air active control system.

8. A gas turbine engine characterized by, The combustion chamber according to any one of claims 5 to 7 is provided.

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