CN210859342U - Gas compressor and air guide groove flow guide control structure thereof - Google Patents
Gas compressor and air guide groove flow guide control structure thereof Download PDFInfo
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- CN210859342U CN210859342U CN201921808269.7U CN201921808269U CN210859342U CN 210859342 U CN210859342 U CN 210859342U CN 201921808269 U CN201921808269 U CN 201921808269U CN 210859342 U CN210859342 U CN 210859342U
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Abstract
An object of the utility model is to provide a compressor and bleed air groove water conservancy diversion control structure thereof to improve the flow of bleed air current. The guiding control structure of the air compressor air guiding groove comprises a flow passage wall surface and an air guiding groove on the flow passage wall surface, wherein a plurality of air guiding flow deflectors are arranged in the air guiding groove along the circumferential direction, each air guiding flow deflector is provided with a bottom end, a top end, a front edge and a rear edge, the bottom end is fixed on the upstream wall surface side or the downstream wall surface side of the air guiding groove, the top end faces the downstream wall surface side or the upstream wall surface side of the air guiding groove in a protruding mode, the front edge is located on the air inlet side of the air guiding groove, the rear edge is located on the air outlet side of the air guiding groove, the air guiding flow deflectors are of an airfoil structure, and the top ends of the air guiding flow deflectors and the downstream wall surface side or the upstream wall surface side of.
Description
Technical Field
The utility model relates to a compressor especially relates to from bleed mechanism of runner bleed air of compressor.
Background
In order to meet the requirements of airplane flight and normal operation of an engine, an aircraft engine usually performs air bleed from an interstage of a high-pressure compressor. The extracted gas is used for cooling of turbine blades, cabin air supply, aircraft anti-icing, sealing of clearance structures, providing a high pressure environment for fuel tanks and other accessory equipment, etc. The air-bleed holes or air-bleed grooves are usually located on the wall surface of a flow passage of the intermediate stage or the outlet stage of the compressor. The grooving method for the wall surface has the following problems: the air-entraining structures with grooves on the wall surfaces are communicated in the whole circumferential direction of the air compressor, when gas flows out of the air-entraining grooves, the circumferential flowing space of fluid is large, the gas easily flows in the circumferential direction, and further an undesirable flowing structure is possibly generated to influence the air-entraining flowing and the main flow in the air compressor.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a compressor and bleed air groove water conservancy diversion control structure thereof to improve the flow of bleed air current.
The utility model provides a compressor bleed air groove water conservancy diversion control structure includes the bleed air groove on runner wall surface and the runner wall surface, be provided with a plurality of bleed air deflectors along circumference in the bleed air groove, the bleed air deflector has bottom and top, leading edge and trailing edge, the bottom is fixed on the upstream wall face side or the downstream wall face side of bleed air groove, the top is towards the protruding setting of downstream wall face side or the upstream wall face side of bleed air groove, the leading edge is located the side of admitting air of bleed air groove, the trailing edge is located the side of bleeding air groove, the bleed air deflector is the airfoil structure, and its top with the downstream wall face side or the upstream wall face side of bleed air groove have the clearance.
In one or more embodiments of the flow guide structure of the compressor bleed air groove, the leading edge and the trailing edge of the bleed air guide vane are respectively pointed and blunt.
In one or more embodiments of the flow control structure of the compressor bleed air duct, a joint between the bottom end of the bleed air deflector and the upstream wall surface side or the downstream wall surface side of the bleed air duct is a thickened structure.
In one or more embodiments of the flow guide control structure of the air compressor bleed air groove, the top end of the bleed air guide vane is pointed.
In one or more embodiments of the flow guide structure of the air compressor bleed air groove, the bleed air guide vane is of an airfoil structure, and the side surfaces of the two sides of the bleed air guide vane are both convex curved surfaces.
In one or more embodiments of the compressor bleed slot flow guide control structure, the gap is 3% to 10% of the width of the bleed slot.
In one or more embodiments of the flow guide control structure of the compressor bleed air groove, the bleed air groove surrounds the entire circumference of the flow passage wall surface.
In one or more embodiments of the flow guide control structure of the air compressor bleed air groove, the wall surface of the flow passage is a middle-stage casing of the high-pressure air compressor, and is a corresponding wall surface between an upstream stator blade and a downstream rotor blade, and the air outlet side of the bleed air groove corresponds to the bleed air-collecting cavity of the middle-stage casing.
In one or more embodiments of the flow guide control structure of the air compressor bleed air groove, the wall surface of the flow passage is a corresponding wall surface between the outlet of the high-pressure air compressor and the outlet cutoff blade, and the air outlet side of the bleed air groove corresponds to the inner ring cavity and the outer ring cavity of the diffuser.
The compressor comprises any one of the gas compressor air guide groove flow guide control structures.
The flow guide control structure of the gas leading groove of the compressor has the beneficial effects that:
1. the flow of the gas in the air-entraining groove is guided by the flow deflector structure in the air-entraining groove, so that the possibility of generating unfavorable flow structures such as separation, backflow or vortex and the like due to the flow is reduced, the flow loss is reduced, and the flow efficiency is improved;
2. after the flow in the groove is improved through the flow deflector structure in the air guide groove, the adverse effect of the gas flow in the air guide groove on the main flow in the flow channel of the compressor can be reduced;
3. after the flow in the groove is improved through the flow deflector structure in the air guide groove, the influence of the wall surface air guide structure on the performance of the air compressor can be weakened when the air compressor is in certain severe working conditions.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:
FIG. 1 is a schematic diagram of a flow guide control structure of a bleed air groove of a compressor.
Fig. 2 is a schematic view along a-a in fig. 1.
Fig. 3 is a schematic view along the direction B-B in fig. 1.
Fig. 4 is a schematic diagram of the first embodiment.
Fig. 5 is a schematic diagram of the second embodiment.
Detailed Description
The following discloses many different embodiments or examples for implementing the subject technology described. Specific examples of components and arrangements are described below to simplify the present disclosure, but these are merely examples and do not limit the scope of the invention. For example, if a first feature is formed over or on a second feature described later in the specification, this may include embodiments in which the first and second features are formed in direct contact, and may also include embodiments in which additional features are formed between the first and second features, such that the first and second features may not be in direct contact. Additionally, reference numerals and/or letters may be repeated among the various examples throughout this disclosure. This repetition is for the purpose of simplicity and clarity and does not in itself dictate a relationship between the various embodiments and/or configurations discussed. Further, when a first element is described as being coupled or coupled to a second element, the description includes embodiments in which the first and second elements are directly coupled or coupled to each other, as well as embodiments in which one or more additional intervening elements are added to indirectly couple or couple the first and second elements to each other.
As shown in fig. 1 to 3, the flow control structure of the compressor bleed slot includes a flow channel wall surface and a bleed slot 5 on the flow channel wall surface, the flow channel wall surface is an outer casing between an upstream blade 1 and a downstream blade 2 of the compressor, the bleed slot is circumferentially communicated with each other, i.e., surrounds the entire circumference of the outer casing, and the upstream outer casing 3 and the downstream outer casing 4 are connected by other structures not shown in the figures. The bleed slot 5 thus has an upstream wall 51 and a downstream wall 52, the upstream wall 51 and the downstream wall 52 defining a bleed air passage. A plurality of bleed air guide vanes 6 are arranged in the bleed air channel 5. The air guide flow deflectors are arranged in the air guide grooves to guide air flow to flow, so that the flow field is improved. Specifically, the bleed air deflector 6 is arranged on one side of the upstream wall surface 51 in the bleed air groove 5, and a certain gap is left between the bleed air deflector 6 and the downstream wall surface 52, wherein the gap is 3% -10% of the width of the bleed air groove 5. The width of the gas introduction groove 5 is the distance between the upstream wall surface 51 and the downstream wall surface 52.
As shown in fig. 2 and 3, the bleed guide vane 6 has a leading edge 61, a trailing edge 62 and two sides 63, 64, a bottom end 65 and a top end 66. The bottom end 65 is fixed to the upstream wall 51 and the top end 66 projects toward the downstream wall 52. In another embodiment, the bottom end 65 is fixed to the downstream wall and the top end 66 projects toward the upstream wall. The tip 66 has a gap with its opposing wall surface. Both side surfaces 63, 64 are convex curved surfaces.
As shown in the a-a view of fig. 2, the bleed air deflector 6 is an airfoil shaped structure with a blade profile design, with a pointed leading edge and a blunt trailing edge. The blunt tip is relative to the shape of the leading edge of the guide vane 6.
As shown in the cross section B-B of fig. 3, the thickness of the bottom end of the guide vane 6, which is connected to the upstream casing 3, i.e., the upstream wall 51, is slightly increased to be a thickened structure, i.e., thicker than the adjacent guide vane, and the top end of the guide vane, which is close to the downstream casing 4, is pointed.
Implementation mode one
Referring to fig. 4, the first embodiment is a flow guiding control structure of a gas guiding groove of a high-pressure compressor, which is located at a gas guiding position of a middle-stage casing of the high-pressure compressor. Wherein 8 is an upstream stator blade, 9 is a downstream rotor blade, 10 is a wall surface air guide groove of an outer flow passage of the compressor, 11 is a gas guide blade of the compressor, and 12 is an intermediate casing gas guide and collection cavity. The incoming flow gas flows from upstream to downstream, part of the gas is guided away from the air guide groove 10 on the wall surface of the outer runner, and the guided gas flows through the guide vanes 11 of the air guide groove to be rectified, flows into the air guide and gas collection cavity of the intermediate casing, and then flows to other places through other pipelines for cooling the turbine of the engine, preventing the ice at the inlet of the engine, using the air for the client air conditioner in the cabin of the airplane and the like. The guide vanes 11 of the air guide grooves rectify the flow of the air guide, improve the gas flow field at the air guide grooves, and reduce the possibility of unfavorable flow structures such as separation, backflow, vortex and the like, thereby reducing the flow loss and improving the flow efficiency.
Second embodiment
Referring to fig. 5, the second embodiment is a flow guide control structure of a bleed air groove of a compressor, which is located at the outlet of the high-pressure compressor and at the front edge of an OGV (outlet guide vane) blade. The rotor blade 13 is an upstream rotor blade, the OGV stator blade 14 is a downstream OGV stator blade, the OGV outlet air guide groove 15 is an OGV outlet air guide groove, the air compressor air guide vane 16 is an air compressor air guide vane, and the diffuser inner and outer ring cavities 17 are arranged. The incoming flow gas is guided away from the outlet of the compressor interstage runner at the air guide groove 15 in front of the OGV of the wall surface of the outer runner, the guided gas flows through the guide vanes 16 of the air guide groove, is rectified, flows into the intermediate casing, is guided and collected, and then flows to the turbine of the engine through other pipelines for cooling the turbine. The guide vanes 16 of the air guide grooves rectify the flow of the air guide, improve the gas flow field at the air guide grooves, and reduce the possibility of unfavorable flow structures such as separation, backflow, vortex and the like, thereby reducing the flow loss and improving the flow efficiency.
The foregoing embodiments may address at least one of the following issues:
1. in the traditional wall surface air guide groove mode, the flow of air in the air guide groove is lack of guidance, the flow speed and the flow direction are spontaneously formed, unfavorable flow structures such as separation, vortex and backflow can be generated, the flow loss is generated, and the efficiency is influenced;
2. due to the defects, the main flow in the flow channel of the air compressor can be adversely affected by the flow of separation, backflow, vortex and the like in the air-entraining groove;
3. due to the defects, under certain severe working conditions of the compressor, the gas flow in the wall surface gas guiding groove can have adverse effects on the performance of the compressor.
Aiming at the problem that the air flow in the air guide groove structure on the wall surface of the air compressor is lack of flow guide, the air guide flow deflectors are arranged in the air guide groove along the radial direction to guide the air flow in the air guide groove, so that the flow in the air guide groove is improved, and the following beneficial effects can be achieved:
1. the flow of the gas in the air-entraining groove is guided by the flow deflector structure in the air-entraining groove, so that the possibility of generating unfavorable flow structures such as separation, backflow, vortex and the like due to the flow is reduced, the flow loss is reduced, and the flow efficiency is improved;
2. after the flow in the groove is improved through the flow deflector structure in the air guide groove, the adverse effect of the gas flow in the air guide groove on the main flow in the flow channel of the compressor can be reduced;
3. after the flow in the groove is improved through the flow deflector structure in the air guide groove, the influence of the wall surface air guide structure on the performance of the air compressor can be weakened when the air compressor is in certain severe working conditions.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent changes and modifications made to the above embodiments according to the technical spirit of the present invention, all without departing from the content of the technical solution of the present invention, fall within the scope of protection defined by the claims of the present invention.
Claims (10)
1. The guiding control structure of the air guiding groove of the air compressor comprises a flow passage wall surface and an air guiding groove on the flow passage wall surface, and is characterized in that a plurality of air guiding guide vanes are arranged in the air guiding groove along the circumferential direction, each air guiding guide vane is provided with a bottom end, a top end, a front edge and a rear edge, the bottom end is fixed on the upstream wall surface side or the downstream wall surface side of the air guiding groove, the top end faces the downstream wall surface side or the upstream wall surface side of the air guiding groove in a protruding mode, the front edge is located on the air inlet side of the air guiding groove, the rear edge is located on the air outlet side of the air guiding groove, each air guiding guide vane is of an airfoil structure, and the top end of each air guiding vane is provided with a gap on the downstream wall surface side or.
2. The compressor bleed slot flow control structure of claim 1 wherein said leading and trailing edges of said bleed guide vanes are pointed and blunt, respectively.
3. The compressor bleed air chute flow guide control structure of claim 1 wherein the connection of the bottom end of the bleed air deflector to the upstream or downstream wall face side of the bleed air chute is a thickened structure.
4. The compressor bleed air chute flow guide control structure of claim 3 wherein the top end of the bleed air guide vanes are pointed.
5. The compressor bleed air chute flow guide control structure of claim 1 wherein the bleed air guide vanes are of an airfoil configuration with convex curved sides on both sides.
6. The compressor bleed slot flow control arrangement of claim 1 wherein the gap is between 3% and 10% of the width of the bleed slot.
7. The compressor bleed air groove flow guide control structure of claim 1 wherein the bleed air groove extends around the entire circumference of the flow path wall.
8. The compressor bleed air duct flow guide control structure of claim 1 wherein the flow path wall is a high pressure compressor mid-stage casing and is a corresponding wall between the upstream stator blade and the downstream rotor blade, and the air outlet side of the bleed air duct corresponds to the intermediate casing bleed air collection cavity.
9. The compressor bleed air groove flow guide control structure as claimed in claim 1, wherein the wall surface of the flow passage is a corresponding wall surface between the outlet of the high pressure compressor and the outlet flow cutoff blade, and the air outlet side of the bleed air groove corresponds to the inner ring cavity and the outer ring cavity of the diffuser.
10. A compressor comprising a compressor bleed air groove flow guide control structure as claimed in any one of claims 1 to 9.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201921808269.7U CN210859342U (en) | 2019-10-25 | 2019-10-25 | Gas compressor and air guide groove flow guide control structure thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201921808269.7U CN210859342U (en) | 2019-10-25 | 2019-10-25 | Gas compressor and air guide groove flow guide control structure thereof |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112065774A (en) * | 2020-09-15 | 2020-12-11 | 中国航发沈阳发动机研究所 | Cartridge receiver structure and rotor-stator structure thereof |
| CN112901342A (en) * | 2021-03-17 | 2021-06-04 | 北京航空航天大学 | Air entraining structure of air compressor |
| CN113847279A (en) * | 2021-09-27 | 2021-12-28 | 中国航发沈阳发动机研究所 | Low pressure compressor part bleed structure |
| CN113931882A (en) * | 2021-12-16 | 2022-01-14 | 中国航发上海商用航空发动机制造有限责任公司 | Compressor, aircraft engine and aircraft |
| CN114396324A (en) * | 2021-12-27 | 2022-04-26 | 哈尔滨工程大学 | Shrouded blade with casing having cooling channel-groove seal-bendable sealing strip composite structure |
| CN115013837A (en) * | 2022-05-12 | 2022-09-06 | 中国航发四川燃气涡轮研究院 | Be used for aeroengine combustion chamber diffuser bleed structure |
-
2019
- 2019-10-25 CN CN201921808269.7U patent/CN210859342U/en active Active
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112065774A (en) * | 2020-09-15 | 2020-12-11 | 中国航发沈阳发动机研究所 | Cartridge receiver structure and rotor-stator structure thereof |
| CN112901342A (en) * | 2021-03-17 | 2021-06-04 | 北京航空航天大学 | Air entraining structure of air compressor |
| CN112901342B (en) * | 2021-03-17 | 2022-06-24 | 北京航空航天大学 | Air entraining structure of air compressor |
| CN113847279A (en) * | 2021-09-27 | 2021-12-28 | 中国航发沈阳发动机研究所 | Low pressure compressor part bleed structure |
| CN113847279B (en) * | 2021-09-27 | 2024-04-19 | 中国航发沈阳发动机研究所 | Bleed structure of low-pressure compressor component |
| CN113931882A (en) * | 2021-12-16 | 2022-01-14 | 中国航发上海商用航空发动机制造有限责任公司 | Compressor, aircraft engine and aircraft |
| CN114396324A (en) * | 2021-12-27 | 2022-04-26 | 哈尔滨工程大学 | Shrouded blade with casing having cooling channel-groove seal-bendable sealing strip composite structure |
| CN115013837A (en) * | 2022-05-12 | 2022-09-06 | 中国航发四川燃气涡轮研究院 | Be used for aeroengine combustion chamber diffuser bleed structure |
| CN115013837B (en) * | 2022-05-12 | 2023-08-18 | 中国航发四川燃气涡轮研究院 | Be used for aeroengine combustion chamber diffuser bleed air structure |
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