CN112178690A

CN112178690A - Combustion chamber casing

Info

Publication number: CN112178690A
Application number: CN202010990124.4A
Authority: CN
Inventors: 时远; 赵弦; 宋宇佳; 郭凯; 曾宇晖; 何鹏; 邓远灏; 李九龙; 张伟; 卢加平; 徐兵; 姜山
Original assignee: AECC Sichuan Gas Turbine Research Institute
Current assignee: AECC Sichuan Gas Turbine Research Institute
Priority date: 2020-09-18
Filing date: 2020-09-18
Publication date: 2021-01-05
Anticipated expiration: 2040-09-18
Also published as: CN112178690B

Abstract

The invention belongs to the field of aero-engines, particularly relates to the field of aero-engines for small bombs, and particularly relates to a combustion chamber casing. The compressor stator blade assembly comprises an outer casing assembly, an inner casing assembly and a compressor last-stage stator blade group; the outer casing component is connected with the inner casing component through a last-stage stator blade group of the compressor; the inner cartridge assembly comprises a compressor bearing seat, a turbine bearing seat and at least two groups of inner cartridge barrels; each inner cartridge barrel is sleeved between a compressor bearing seat and a turbine bearing seat in a layered manner, the compressor bearing seat is provided with an air inlet, and the turbine bearing seat is provided with an air outlet; an air channel between the air inlet and the air outlet is formed between the inner cartridge body. The combustor casing layout structure is high in function integration level, effectively utilizes the space of an engine, greatly shortens the axial length of the engine, lightens the weight of the engine, and achieves low cost and high performance of the engine.

Description

Combustion chamber casing

Technical Field

The invention belongs to the field of aero-engines, particularly relates to the field of aero-engines for small bombs, and particularly relates to a combustion chamber casing.

Background

Since the 70 s of the 20 th century, the rapid development of cruise missile technology has profound impact on modern war. Particularly, since the 90's gulf war, various local warfare and regional conflicts in the world, such as the kosowa war, the meyan war, the libria war, the syrian conflict, and the like, have fully demonstrated the important role of precisely guided missiles in modern warfare.

One of the key technologies of the cruise missile is the development of a small-sized high-performance low-cost aero-engine. Currently, in this class of engine research, the most representative are the american F107 series, which is mainly used for "axe" cruise missiles, and the french TRI60 series, which is used for a variety of drones and missiles.

In view of the great success of the development and the use of the small-sized missile aeroengine in China and the great prospect of the air-breathing cruise missile in the future modernization war. The related development work of the small-sized missile aeroengine plays an important role in the military and modernization industry of China.

The combustion chamber is positioned between the air compressor and the turbine, and has the functions of mixing and combusting fuel oil sprayed by the fuel oil nozzle and high-pressure air from the air compressor, converting chemical energy of the fuel into heat energy, ensuring the given temperature of the fuel gas at the inlet of the turbine and improving the capability of the fuel gas for expanding and doing work in the turbine and the tail nozzle.

The combustor casing is an important component of a combustor part, forms an airflow channel of the combustor, provides positioning support for other combustor components, and is one of main bearing parts of an engine. Different from the traditional aeroengine, the missile engine is a disposable product, and the required cost is low; meanwhile, due to the requirements of anti-reconnaissance and missile loading, the device has higher pursuit in the aspects of small volume and light weight.

Because of the inheritance of engine development, the existing small-sized engines mostly adopt a baffling type and backflow type combustion chamber matched centrifugal compressor structure. With the continuous progress of the anti-guidance system, the speed and anti-reconnaissance requirements of the missile are higher and higher. However, both combustion chambers have a pressure loss that increases with increasing velocity, while being dimensionally short in axial length and large in radial profile. Therefore, the direct-flow combustion chamber structure matched with the axial-flow compressor gradually becomes the main research direction of the small-sized elastic aircraft engine in the new period due to the advantages of the direct-flow combustion chamber structure in the high-speed state and the characteristic of small frontal area.

Disclosure of Invention

With the further improvement of the performance requirements of the small-sized missile-used engine, the aims of small size and light weight are pursued, the limitation and the defect of the prior art are further overcome, and the combustion chamber casing with highly integrated functions is provided for the straight-flow combustion chamber of the small-sized missile-used aero-engine. The problem that more functions are realized to the combustion chamber machine casket of mainly solving less space to guarantee structural design safe and reliable, can use effectively in the design of small-size aeroengine for bullet.

In order to achieve the technical purpose, the invention adopts the following specific technical scheme:

a combustion chamber casing comprises an outer casing component, an inner casing component and a compressor final-stage stator blade group; the outer casing component is connected with the inner casing component through the last-stage stator blade group of the compressor; the inner casing assembly comprises a compressor bearing seat, a turbine bearing seat and at least two groups of inner casing barrels;

each inner casing barrel is sleeved between the compressor bearing seat and the turbine bearing seat in a layered mode, the compressor bearing seat is provided with an air inlet, and the turbine bearing seat is provided with an air outlet; and an air channel between the air inlet and the air outlet is formed between the inner casing bodies.

Further, the compressor last stage stator blade set includes a plurality of last stage stator blades; and the last-stage stator blades are uniformly distributed between the outer casing component and the inner casing component in the circumferential direction and are all arranged in the diffuser.

Furthermore, each compressor last-stage stator blade is welded in the diffuser.

Furthermore, a through hole is formed in the bearing seat of the compressor, and the combustion chamber casing also comprises a lubricating oil pipeline; the lubricating oil pipeline comprises an oil pipe joint and a lubricating oil pipe which are communicated with each other; the lubricating oil pipe is fixed on the compressor bearing seat and communicated with a lubricating oil nozzle through the through hole; the lubricating oil nozzle is used for lubricating and cooling the rotor bearing.

Furthermore, the outside cover of slide oil pipe is equipped with thermal-insulated protective sheath.

Further, the through holes are 1-3 groups.

Further, the inner cartridge assembly includes three sets of inner cartridge bodies.

Furthermore, the thickness of the inner cartridge body is 0.8-1.5 mm.

Furthermore, the gap between the inner casing barrels is 3-15 mm.

By adopting the technical scheme, the invention can bring the following beneficial effects:

the invention relates to a combustion chamber casing structure with highly integrated functions. The casing is suitable for a straight-flow annular combustion chamber. The casing layout structure not only has the important force transmission, positioning and centering functions of an engine, but also integrates last-stage stator blades, and realizes the air inlet rectification and diffusion functions of a combustion chamber with the inner wall and the outer wall of a diffuser; an engine bearing seat and a bearing lubricating oil path assembly are integrated, so that the supporting, positioning and lubricating functions of the engine bearing are realized; meanwhile, a flow path component of an engine air system is integrated, and the functions of sealing the flow path of the air system and cooling and air entraining of the turbine are realized.

The combustor casing layout structure is high in function integration level, effectively utilizes the space of an engine, greatly shortens the axial length of the engine, lightens the weight of the engine, and achieves low cost and high performance of the engine.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present disclosure, the drawings needed to be used in the embodiments will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present disclosure, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.

FIG. 1 is a schematic view of a functionally highly integrated combustor casing;

FIG. 2 is a schematic view of an inner housing assembly;

FIG. 3 is a schematic view of the arrangement of the oil tube and oil support in the combustion chamber casing.

Wherein: 1-outer casing component, 11-outer casing front section, 12-outer casing barrel, 13-outer casing rear section, 14-nozzle mounting seat, 15-igniter mounting seat; 2-inner casing component, 20-outer layer channel, 21-compressor bearing seat, 22-turbine bearing seat, 23-outer layer cylinder, 24-middle cylinder, 25-inner layer cylinder, 26-lubricating oil bracket, 27-air inlet hole, 28-air outlet hole and 29-inner layer channel; 3-diffuser with compressor last stage stator blade, 31-compressor last stage stator blade; 4-lubricating oil channel, 40-lubricating oil channel, 41-oil pipe joint, 42-lubricating oil pipe and 43-heat insulation protective sleeve.

Detailed Description

The embodiments of the present disclosure are described in detail below with reference to the accompanying drawings.

The embodiments of the present disclosure are described below with specific examples, and other advantages and effects of the present disclosure will be readily apparent to those skilled in the art from the disclosure in the specification. It is to be understood that the described embodiments are merely illustrative of some, and not restrictive, of the embodiments of the disclosure. The disclosure may be embodied or carried out in various other specific embodiments, and various modifications and changes may be made in the details within the description without departing from the spirit of the disclosure. It is to be noted that the features in the following embodiments and examples may be combined with each other without conflict. All other embodiments, which can be derived by a person skilled in the art from the embodiments disclosed herein without making any creative effort, shall fall within the protection scope of the present disclosure.

It is noted that various aspects of the embodiments are described below within the scope of the appended claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the disclosure, one skilled in the art should appreciate that one aspect described herein may be implemented independently of any other aspects and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. Additionally, such an apparatus may be implemented and/or such a method may be practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.

It should be noted that the drawings provided in the following embodiments are only for illustrating the basic idea of the present disclosure, and the drawings only show the components related to the present disclosure rather than the number, shape and size of the components in actual implementation, and the type, amount and ratio of the components in actual implementation may be changed arbitrarily, and the layout of the components may be more complicated.

In addition, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects may be practiced without these specific details.

In one embodiment, as shown in fig. 1, the structure of a combustor casing is schematically illustrated, and comprises an outer casing component 1, an inner casing component 2 and a compressor last stage stator blade set; the outer casing component 1 and the inner casing component 3 are connected through a last-stage stator blade group of the compressor; the inner cartridge assembly 1 comprises a compressor bearing seat 21, a turbine bearing seat 22 and at least two groups of inner cartridge bodies;

each inner cartridge barrel is sleeved between the compressor bearing seat 21 and the turbine bearing seat 22 in a layered manner, the compressor bearing seat 21 is provided with an air inlet, and the turbine bearing seat is provided with an air outlet; an air channel between the air inlet and the air outlet is formed between the inner cartridge body.

The outer casing assembly 1 is composed of an outer casing front section 11, an outer casing barrel 12 and an outer casing rear section 13. 12-16 nozzle installation seats 14 are uniformly distributed on the outer cartridge case component 1 along the circumferential direction and used for installing fuel nozzles, and meanwhile, a hole is formed in each installation seat and used for enabling the nozzle to extend into the cartridge case for supplying oil. In addition, 2-3 igniter installing seats 15 are further distributed on the outer casing assembly 1 along the circumferential direction and used for installing an igniter or an electric nozzle, and meanwhile, a hole is formed in each installing seat and used as a channel to conduct ignition or enable the electric nozzle to stretch into the inner portion of the casing.

The inner cartridge assembly 2 is formed by connecting a compressor bearing seat 21 and a turbine bearing seat 22 through 3 layers of cartridge bodies.

The combustion chamber casing adopts an internal and external mixed force transmission mode, axial force is shared, and the wall thickness of the casing is reduced to the maximum extent; and the inner casing is designed into a three-layer thin plate structure, so that the inner casing with a smaller diameter has enough radial rigidity. The sheet material can reduce the cost while effectively reducing the weight.

In one embodiment, the compressor last stage stator blade set includes a plurality of last stage stator blades 31; the last-stage stator blades are uniformly distributed between the outer casing component 1 and the inner casing component 2 in the circumferential direction and are all arranged in the diffuser. The last-stage stator blades 31 of each compressor are welded in the diffuser.

In the present embodiment, the outer casing front section 11 and the compressor bearing seat 21 together form an outer flow passage and an inner flow passage of the diffuser 3, and the outer flow passage and the inner flow passage are connected into a whole through the compressor last-stage stator blades 31. The diffuser and the last-stage stator blade of the compressor are integrally designed, the traditional diffuser support plate structure is simplified, and the diffuser and the last-stage stator blade of the compressor have positive significance for reducing weight, shortening the length of an engine and improving the critical rotating speed of a rotor.

In one embodiment, in order to simultaneously meet the requirements of light weight and strength of the inner cartridge assembly, the inner cartridge assembly 2 comprises three sets of inner cartridge barrels, the thickness of the inner cartridge barrels is 0.8-1.5 mm, and the gap between the inner cartridge barrels is 3-15 mm.

The 3-layer inner casing body on the inner casing assembly forms 2 airflow channels. Taking the outer channel 20 as an example: the compressor bearing seat 21 is provided with a plurality of air inlet holes 27 along the circumference, a gap is arranged between the outer layer cylinder 23 and the middle layer cylinder 24, and the turbine bearing seat 22 is provided with a plurality of air outlet holes 28 along the circumference, so that a complete air flow channel is formed. The inner layer channel 29 is identical in construction to the outer layer channel 20. The embodiment integrates the flow path assembly of the engine air system, and realizes the functions of sealing the flow path of the air system and cooling and air-entraining of the turbine.

In this embodiment, the compressor bearing seat 21 on the inner cartridge assembly 2 provides a support seat for the compressor rear bearing 51, and the turbine bearing seat 22 provides a support seat for the turbine front bearing 52. The design that the engine rotor support is positioned on the combustion chamber casing can effectively shorten the length of the engine and simplify the rear bearing structure.

In one embodiment, as shown in fig. 3, the compressor bearing seat 21 is provided with a through hole, and the combustion chamber casing further comprises a lubricating oil pipeline 4; the oil slide pipe 4 comprises an oil pipe joint 41 and an oil slide pipe 42 which are communicated with each other; the lubricating oil pipe 42 is fixed on the compressor bearing seat 21 and communicated with a lubricating oil nozzle through a through hole; the oil spray nozzle is used for lubricating and cooling the rotor bearing.

The outside of the oil slide is sleeved with a heat insulation protective sleeve 43.

The through holes are 1-3 groups, and each group of through holes is provided with a lubricating oil pipeline 4.

In this embodiment, the combustor casing further has 1 to 3 lubricating oil conduits 4. The oil pipe 42 penetrates through the outer cartridge assembly 1 and is welded on the compressor bearing seat 21 of the inner cartridge assembly 2. The oil conduit 42 forms an oil passage 40 with the bore in the compressor bearing housing 21. In addition, the oil pipe joint 41 is used for being connected with an oil supply pipeline, and the heat insulation protective sleeve 43 is used for isolating high-temperature gas in the combustion chamber, so that the phenomenon that the working performance of lubricating oil is affected due to the fact that the temperature of the lubricating oil is increased too fast is avoided. On the inner barrel 25 of the inner casing assembly 2 there is an oil support 26 for mounting the nozzle of the oil system. The rotor bearing can be cooled and lubricated by supplying oil through the lubricating oil channel 40.

The above description is only for the specific embodiments of the present disclosure, but the scope of the present disclosure is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present disclosure should be covered within the scope of the present disclosure. Therefore, the protection scope of the present disclosure shall be subject to the protection scope of the claims.

Claims

1. A combustor case, comprising: the compressor stator blade assembly comprises an outer casing assembly, an inner casing assembly and a compressor last-stage stator blade group; the outer casing component is connected with the inner casing component through the last-stage stator blade group of the compressor; the inner casing assembly comprises a compressor bearing seat, a turbine bearing seat and at least two groups of inner casing barrels;

2. The combustor casing of claim 1, wherein: the compressor last-stage stator blade group comprises a plurality of last-stage stator blades; and the last-stage stator blades are uniformly distributed between the outer casing component and the inner casing component in the circumferential direction and are all arranged in the diffuser.

3. The combustor casing of claim 2, wherein: and the last-stage stator blades of the compressor are welded in the diffuser.

4. The combustor casing of claim 1, wherein: the gas compressor bearing block is provided with a through hole, and the combustion chamber casing also comprises a lubricating oil pipeline; the lubricating oil pipeline comprises an oil pipe joint and a lubricating oil pipe which are communicated with each other; the lubricating oil pipe is fixed on the compressor bearing seat and communicated with a lubricating oil nozzle through the through hole; the lubricating oil nozzle is used for lubricating and cooling the rotor bearing.

5. The combustor casing of claim 4, wherein: and a heat insulation protective sleeve is sleeved outside the oil sliding pipe.

6. The combustor casing of claim 4, wherein: the through holes are 1-3 groups.

7. The combustor casing of claim 1, wherein: the inner cartridge assembly includes three inner cartridge body sets.

8. The combustor casing of claim 7, wherein: the thickness of the inner casing barrel is 0.8-1.5 mm.

9. The combustor casing of claim 8, wherein: the gap between the inner casing barrels is 3-15 mm.