CN113638775A - Pre-rotation nozzle structure with bypass air entraining - Google Patents
Pre-rotation nozzle structure with bypass air entraining Download PDFInfo
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- CN113638775A CN113638775A CN202111190025.9A CN202111190025A CN113638775A CN 113638775 A CN113638775 A CN 113638775A CN 202111190025 A CN202111190025 A CN 202111190025A CN 113638775 A CN113638775 A CN 113638775A
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- Prior art keywords
- bleed air
- bypass
- air channel
- bypass bleed
- diameter cavity
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides a pre-rotation nozzle structure with bypass air entraining, which comprises an inner support of a guider, wherein the pre-rotation nozzle structure with the bypass air entraining comprises a plurality of pre-rotation nozzle blades, each pre-rotation nozzle blade is integrally formed with the inner support of the guider, a main flow air entraining channel is formed between every two adjacent pre-rotation nozzle blades, and a bypass air entraining channel is arranged in each pre-rotation nozzle blade. The guide vane structure has the beneficial effects that the pre-rotation nozzle vane, the main flow air guide channel and the bypass air guide channel are designed in a fusion mode, so that the pre-rotation nozzle vane and the inner support of the guider are integrally formed, and the problems that an air guide pipe is difficult to install, the weight is heavy and the inlet flow field of the pre-rotation nozzle vane is uneven in the prior art are solved.
Description
Technical Field
The invention relates to the field of aircraft engines, in particular to a pre-rotation nozzle structure with bypass air entraining.
Background
The pre-swirl nozzle structure is a commonly used pre-disc bleed air structure in aircraft engines. Generally, the structure consists of a pre-rotation nozzle inlet gas collection cavity, a pre-rotation nozzle flow passage and pre-rotation nozzle blades.
In the prior art, bypass air-entraining generally adopts an air-entraining pipe arranged at an inlet air-collecting cavity. However, this structure has the following problems:
1. The air guide pipe is difficult to install and position, the number of parts is large, and the weight is heavy;
2. the number of the air guide pipes is far smaller than that of the pre-rotation nozzle blades, so that the flow field is uneven;
3. the bleed pipe can occupy import gas-collecting chamber space, causes great flow loss, influences air feed pressure.
Disclosure of Invention
The invention provides a pre-rotation nozzle structure with bypass bleed air, which aims to solve the problem of uneven inlet flow field.
The technical scheme adopted by the invention for solving the technical problems is as follows: the utility model provides a take prewhirl nozzle structure of bypass bleed, includes that the director supports, takes the prewhirl nozzle structure of bypass bleed to include a plurality of prewhirl nozzle vanes, and every prewhirl nozzle vane all with the director in support integrated into one piece, form mainstream bleed passageway between two adjacent prewhirl nozzle vanes, all be provided with bypass bleed passageway in every prewhirl nozzle vane.
Further, an inlet end of the main flow bleed air channel is located at a front side end face of the inner support of the guider, and an outlet end of the main flow bleed air channel is located at a rear side end face of the inner support of the guider.
Furthermore, the mainstream bleed air channel includes first undergauge cavity and first constant diameter cavity, and along mainstream bleed air channel's gas flow direction, the diameter of first undergauge cavity reduces gradually, and the entry of first constant diameter cavity is connected with the path end of first undergauge cavity, and the export of first constant diameter cavity is mainstream bleed air channel's exit end.
Furthermore, the inlet ends of the main flow bleed air channels are uniformly distributed at intervals along the front side end face of the inner support of the guider.
Further, an inlet end of the bypass bleed air channel is located at an inner end face of the inner support of the guide, and an outlet end of the bypass bleed air channel is located at a rear end face of the inner support of the guide.
Furthermore, the bypass bleed air channel comprises a second reducing cavity and a second equal-diameter cavity, the diameter of the second reducing cavity is gradually reduced along the gas flowing direction of the bypass bleed air channel, the inlet end of the bypass bleed air channel is connected with the large-opening end of the second reducing cavity, the inlet of the second equal-diameter cavity is connected with the small-diameter end of the second reducing cavity, and the outlet of the second equal-diameter cavity is the outlet end of the main flow bleed air channel.
Further, the diameter of the inlet end of the bypass bleed air channel is smaller than the diameter of the large opening end of the second reducing cavity.
Further, the inlet ends of the plurality of bypass bleed air channels are evenly distributed at intervals along the inner side end surface of the support in the guider.
Furthermore, the pre-swirl nozzle structure with the bypass bleed air also comprises a mounting part for connecting guide vanes, and the mounting part is arranged on the front side end face of the inner support of the guider and is arranged in a staggered manner with the inlet end of the main flow bleed air channel.
Further, the installation part is a plurality of, sets up along the front side terminal surface of support in the director with interval.
Further, a mounting part is arranged between the inlet ends of two adjacent main flow bleed air channels.
The guide vane structure has the beneficial effects that the pre-rotation nozzle vane, the main flow air guide channel and the bypass air guide channel are designed in a fusion mode, so that the pre-rotation nozzle vane and the inner support of the guider are integrally formed, and the problems that an air guide pipe is difficult to install, the weight is heavy and the inlet flow field of the pre-rotation nozzle vane is uneven in the prior art are solved.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic structural diagram of an embodiment of the present invention;
FIG. 2 is a sectional view taken along line A-A of FIG. 1;
FIG. 3 is a sectional view taken along line B-B of FIG. 1;
fig. 4 is a sectional view taken along line C-C in fig. 1.
Reference numbers in the figures: 1. an installation part; 2. a bypass bleed air passage; 3. a main flow bleed air passage; 4. Pre-spinning the nozzle vanes; 5. an inlet end of a bypass bleed air channel; 6. supporting in the guider; 7. an outlet end of the bypass bleed air passage.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
As shown in fig. 1 to 4, an embodiment of the present invention provides a pre-swirl nozzle structure with bypass bleed air, including a guider inner support 6 and a plurality of pre-swirl nozzle vanes 4, where each pre-swirl nozzle vane 4 is integrally formed with the guider inner support 6, a main bleed air channel 3 is formed between two adjacent pre-swirl nozzle vanes 4, and a bypass bleed air channel 2 is provided in each pre-swirl nozzle vane 4.
According to the embodiment of the invention, the pre-rotation nozzle blade 4, the main stream air-entraining channel 3 and the bypass air-entraining channel 2 are designed in a fusion manner, so that the pre-rotation nozzle blade 4 and the guider inner support 6 are integrally formed, and the problems of difficult installation of an air-entraining pipe, heavy weight and uneven inlet flow field of the pre-rotation nozzle blade 4 in the prior art are solved.
As shown in fig. 4, in this embodiment the inlet end of the main flow bleed air channel 3 is located at the front end face of the inner guide support 6 and the outlet end of the main flow bleed air channel 3 is located at the rear end face of the inner guide support 6. During operation, the main air directly enters the main air guide channel 3 through the inlet of the main air guide channel 3, and then pre-rotation is completed through the pre-rotation nozzle blades 4.
Specifically, the main flow bleed air channel 3 includes a first reducing cavity and a first constant diameter cavity, and along the gas flow direction of the main flow bleed air channel 3, the diameter of the first reducing cavity is gradually reduced, the inlet of the first constant diameter cavity is connected with the small diameter end of the first reducing cavity, and the outlet of the first constant diameter cavity is the outlet end of the main flow bleed air channel 3.
In this embodiment, the first diameter-reducing cavity is connected to the inner wall of the first diameter-reducing cavity by a smooth arc inner wall, so that the purpose that the main flow air-guiding channel 3 cancels the air-collecting cavity is achieved, and the air in the main flow air-guiding channel 3 can smoothly flow.
Preferably, in this embodiment, the inlet ends of the plurality of main flow bleed air channels 3 are evenly spaced along the front end face of the inner support 6 in the guide. Each of the main flow bleed air passages 3 is of identical construction. The plurality of main flow bleed air channels 3 can meet the flow requirement caused by main flow in the implementation, so that the normal working requirement of the aircraft engine can be met in the embodiment.
As shown in figure 3, the inlet end 5 of the bypass bleed air channel is located at the inboard end face of the inner support 6 in the guide and the outlet end 7 of the bypass bleed air channel is located at the rear end face of the inner support 6 in the guide. The bypass bleed air channel 2 is independent of the main stream bleed air channel 3, the bypass bleed air channel 2 is arranged inside the pre-rotation nozzle blade 4, and when the bypass bleed air channel works, the bypass bleed air enters the air collection cavity of the bypass bleed air channel 2 through the inlet end 5 of the bypass bleed air channel and is then discharged through the outlet end 7 of the bypass bleed air channel.
The bypass air-entraining channel 2 comprises a second reducing cavity and a second equal-diameter cavity, the diameter of the second reducing cavity is gradually reduced along the gas flowing direction of the bypass air-entraining channel 2, the inlet end 5 of the bypass air-entraining channel is connected with the large-opening end of the second reducing cavity, the inlet of the second equal-diameter cavity is connected with the small-diameter end of the second reducing cavity, and the outlet of the second equal-diameter cavity is the outlet end 7 of the bypass air-entraining channel.
In this embodiment, the second diameter-reducing cavity forms a gas-collecting cavity of the bypass bleed air channel 2, and the bypass bleed air enters the gas-collecting cavity through an inlet end 5 of the bypass bleed air channel and is then discharged through an outlet end 7 of the bypass bleed air channel.
In particular, the diameter of the inlet end 5 of the bypass bleed air channel is less than the diameter of the large open end of the second reduced diameter cavity. The purpose of adopting above-mentioned structure is that the gas collection ability of reinforcing second undergauge cavity to satisfy the demand of bypass bleed air.
Preferably the inlet ends 5 of the plurality of bypass bleed air channels are equispaced along the inboard end face of the inner support 6 in the guide. The inlet end 5 of the bypass bleed air channel is located so as not to interfere with the normal installation and operation of the other components.
As shown in fig. 1, the pre-swirl nozzle arrangement with bypass bleed air also comprises a mounting 1 for a connecting guide vane, arranged at the front end face of the support 6 in the guide and offset from the inlet end of the main bleed air channel 3. The mounting part 1 is used for connecting a guide vane, so that the guide vane can be fixedly connected with the front end face of the inner support 6 of the guider.
The plurality of mounting portions 1 are provided at intervals along the front end surface of the guide inner support 6. An installation part 1 is arranged between the inlet ends of two adjacent main flow bleed air channels 3. In this embodiment, the installation part 1 is arranged in a manner that stress concentration can be avoided, and uniform stress distribution at the front end face of the inner support 6 of the guider can be ensured.
From the above description, it can be seen that the above-described embodiments of the present invention achieve the following technical effects: according to the embodiment of the invention, the pre-rotation nozzle blade 4, the main stream air-entraining channel 3 and the bypass air-entraining channel 2 are designed in a fusion manner, so that the pre-rotation nozzle blade 4 and the guider inner support 6 are integrally formed, and the problems of difficult installation of an air-entraining pipe, heavy weight and uneven inlet flow field of the pre-rotation nozzle blade 4 in the prior art are solved.
The above description is only exemplary of the invention and should not be taken as limiting the scope of the invention, so that the invention is intended to cover all modifications and equivalents of the embodiments described herein. In addition, the technical features, the technical schemes and the technical schemes can be freely combined and used.
Claims (11)
1. The utility model provides a take in advance of bypass bleed nozzle structure soon, includes and supports (6) in the director, its characterized in that, takes in advance of bypass bleed nozzle structure soon still includes a plurality of nozzle vane (4) soon in advance, and every in advance revolves nozzle vane (4) and all supports (6) integrated into one piece in the director, forms mainstream bleed passageway (3) between two adjacent nozzle vane (4) soon in advance, all is provided with bypass bleed passageway (2) in every nozzle vane (4) soon in advance.
2. The pre-swirl nozzle arrangement with bypass bleed air according to claim 1, characterised in that the inlet end of the main flow bleed air channel (3) is located at the front side end face of the inner deflector support (6) and the outlet end of the main flow bleed air channel (3) is located at the rear side end face of the inner deflector support (6).
3. The pre-swirl nozzle arrangement with bypass bleed air according to claim 2, characterised in that the main bleed air channel (3) comprises a first reduced diameter cavity and a first constant diameter cavity, the diameter of the first reduced diameter cavity decreases gradually in the gas flow direction of the main bleed air channel (3), the inlet of the first constant diameter cavity is connected with the small diameter end of the first reduced diameter cavity, and the outlet of the first constant diameter cavity is the outlet end of the main bleed air channel (3).
4. The pre-swirl nozzle arrangement with bypass bleed air according to claim 2, characterised in that the inlet ends of a plurality of main flow bleed air channels (3) are evenly spaced along the front side end face of the inner support (6) in the deflector.
5. The pre-swirl nozzle arrangement with bypass bleed air according to claim 1, characterised in that the inlet end (5) of the bypass bleed air channel is located at the inboard end face of the inner support (6) of the deflector and the outlet end (7) of the bypass bleed air channel is located at the aft end face of the inner support (6) of the deflector.
6. The pre-swirl nozzle structure with bypass bleed air according to claim 5, characterised in that the bypass bleed air channel (2) comprises a second reduced diameter cavity and a second constant diameter cavity, the diameter of the second reduced diameter cavity is gradually reduced along the gas flow direction of the bypass bleed air channel (2), the inlet end (5) of the bypass bleed air channel is connected with the large opening end of the second reduced diameter cavity, the inlet of the second constant diameter cavity is connected with the small diameter end of the second reduced diameter cavity, and the outlet of the second constant diameter cavity is the outlet end (7) of the bypass bleed air channel.
7. The pre-swirl nozzle arrangement with bypass bleed air according to claim 6 characterised in that the diameter of the inlet end (5) of the bypass bleed air channel is smaller than the diameter of the larger mouth end of the second reduced diameter cavity.
8. The structure of the pre-swirl nozzle with bypass bleed air according to claim 5 characterised in that the inlet ends (5) of the plurality of bypass bleed air channels are equispaced along the inboard end face of the inner support (6) of the deflector.
9. The pre-swirl nozzle arrangement with bypass bleed air according to claim 2, characterised in that it further comprises a mounting (1) for a connecting guide vane, arranged at the front side end face of the support (6) in the guide and offset from the inlet end of the main flow bleed air channel (3).
10. The structure of the pre-swirl nozzle with bypass bleed air according to claim 9, characterised in that the mounting portion (1) is provided in plurality, spaced along the front end face of the inner support (6) in the guide.
11. The pre-swirl nozzle arrangement with bypass bleed air according to claim 10, characterised in that a mounting (1) is provided between the inlet ends of two adjacent main flow bleed air channels (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111190025.9A CN113638775A (en) | 2021-10-13 | 2021-10-13 | Pre-rotation nozzle structure with bypass air entraining |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111190025.9A CN113638775A (en) | 2021-10-13 | 2021-10-13 | Pre-rotation nozzle structure with bypass air entraining |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113638775A true CN113638775A (en) | 2021-11-12 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111190025.9A Pending CN113638775A (en) | 2021-10-13 | 2021-10-13 | Pre-rotation nozzle structure with bypass air entraining |
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| Country | Link |
|---|---|
| CN (1) | CN113638775A (en) |
Citations (11)
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|---|---|---|---|---|
| GB2032531A (en) * | 1978-10-26 | 1980-05-08 | Rolls Royce | Air cooled gas turbine rotor |
| GB8703520D0 (en) * | 1986-05-01 | 1987-03-25 | Gen Electric | Swirl nozzle |
| US6241467B1 (en) * | 1999-08-02 | 2001-06-05 | United Technologies Corporation | Stator vane for a rotary machine |
| US20020028136A1 (en) * | 2000-09-06 | 2002-03-07 | Jan Briesenick | Pre-swirl nozzle carrier |
| US20150121897A1 (en) * | 2013-03-06 | 2015-05-07 | Rolls-Royce North American Technologies, Inc. | Gas turbine engine with soft mounted pre-swirl nozzle |
| US20170044909A1 (en) * | 2015-08-14 | 2017-02-16 | Ansaldo Energia Switzerland AG | Gas turbine cooling systems and methods |
| CN106523037A (en) * | 2016-12-12 | 2017-03-22 | 中国燃气涡轮研究院 | Turbine baffle plate structure with high pre-rotation flowing path |
| CN206581990U (en) * | 2016-12-30 | 2017-10-24 | 中国航发商用航空发动机有限责任公司 | The system of obturaging of prewhirling of aero-engine |
| EP3290636A1 (en) * | 2016-08-29 | 2018-03-07 | United Technologies Corporation | Multi-air stream cooling system |
| CN109458229A (en) * | 2018-12-20 | 2019-03-12 | 中国航发四川燃气涡轮研究院 | A kind of turbine disk chamber seal structure of band bypass bleed |
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2021
- 2021-10-13 CN CN202111190025.9A patent/CN113638775A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2032531A (en) * | 1978-10-26 | 1980-05-08 | Rolls Royce | Air cooled gas turbine rotor |
| GB8703520D0 (en) * | 1986-05-01 | 1987-03-25 | Gen Electric | Swirl nozzle |
| US6241467B1 (en) * | 1999-08-02 | 2001-06-05 | United Technologies Corporation | Stator vane for a rotary machine |
| US20020028136A1 (en) * | 2000-09-06 | 2002-03-07 | Jan Briesenick | Pre-swirl nozzle carrier |
| US20150121897A1 (en) * | 2013-03-06 | 2015-05-07 | Rolls-Royce North American Technologies, Inc. | Gas turbine engine with soft mounted pre-swirl nozzle |
| US20170044909A1 (en) * | 2015-08-14 | 2017-02-16 | Ansaldo Energia Switzerland AG | Gas turbine cooling systems and methods |
| EP3290636A1 (en) * | 2016-08-29 | 2018-03-07 | United Technologies Corporation | Multi-air stream cooling system |
| CN106523037A (en) * | 2016-12-12 | 2017-03-22 | 中国燃气涡轮研究院 | Turbine baffle plate structure with high pre-rotation flowing path |
| CN206581990U (en) * | 2016-12-30 | 2017-10-24 | 中国航发商用航空发动机有限责任公司 | The system of obturaging of prewhirling of aero-engine |
| CN109458229A (en) * | 2018-12-20 | 2019-03-12 | 中国航发四川燃气涡轮研究院 | A kind of turbine disk chamber seal structure of band bypass bleed |
| CN110905606A (en) * | 2019-12-05 | 2020-03-24 | 中国航发四川燃气涡轮研究院 | Turbine disc cavity sealing structure with bypass air entraining function |
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Application publication date: 20211112 |
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| RJ01 | Rejection of invention patent application after publication |