CN110454436A - A kind of short flexure type eddy plate applied to aero-engine compressor high position bleed - Google Patents
A kind of short flexure type eddy plate applied to aero-engine compressor high position bleed Download PDFInfo
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- CN110454436A CN110454436A CN201910690221.9A CN201910690221A CN110454436A CN 110454436 A CN110454436 A CN 110454436A CN 201910690221 A CN201910690221 A CN 201910690221A CN 110454436 A CN110454436 A CN 110454436A
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- Prior art keywords
- bleed
- eddy plate
- compressor
- aero
- air chamber
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/403—Casings; Connections of working fluid especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/58—Cooling; Heating; Diminishing heat transfer
- F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
- F04D29/584—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps cooling or heating the machine
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The application belongs to compressor design field, is related to a kind of short flexure type eddy plate applied to aero-engine compressor high position bleed.The eddy plate (5) setting is in bleed air chamber (4) inward eddy than the position greater than 1, wall surface of eddy plate (5) one end setting in the bleed air chamber (4), the other end extends along compressorshaft into bleed air chamber (4), the eddy plate (5) includes the low radius parts (51) close to compressor axis and high half path portion (52) far from compressor axis, and the low radius parts (51) include to the curved structure in compressor direction of rotation.The present invention is reducing compressor disc chamber bleed resistance, can play obvious action in terms of increasing bleed flow.Have many advantages, such as lightweight and reliability without installation due to using the short twisted plate structure of integration.
Description
Technical field
The application belongs to compressor design field, in particular to a kind of aero-engine compressor high position that is applied to is drawn
The short flexure type eddy plate of gas.
Background technique
Compressor is one of main component of aero-engine, and continuous work is in high temperature, high pressure, high-speed rotating extreme ring
Under border.The cooling scheme that compressor disc generallys use when designing is to extract a certain amount of cold air out through calming the anger from the certain positions of compressor
Machine core axially flows backward, and the heat of compressor disc is taken away, to control the temperature levels and ladder of compressor disc
Spend zone of reasonableness.Since from compressor, radially-inwardly bleed usually requires that centrifugal force and the obstruction of radial coriolis force is overcome to make
With there are certain pressure losses, this will lead to the main channel air flow rate that can be introduced and reduces, and it is cooling to be unfavorable for compressor disc.
Therefore, how to reduce that the drag losses of compressor radial inward flow bleed, to improve bleed flow necessary when being Aeroengine Design
The major issue for considering and solving.
As shown in Figure 1, compressor disc chamber bleed air-flow comes from sprue 1, the air-flow of sprue 1 is introduced between compressor disc
Air collecting chamber 2, then flow radially inwardly into bleed air chamber 4 via the discrete bleed slot 3 in circumferential direction reaches after the low radius of disk chamber again
Two strands are axially subdivided into, one flow forward participates in fulcrum and obturages；Another stock then flows backward, cooling compressor disc.
Compressor radially-inwardly bleed when, the gas of inward flow is diametrically transported due to existing with compressor disc chamber
It is dynamic, a circumferential coriolis force identical with direction of rotation can be generated, under this force, air-flow will be accelerated in the circumferential,
When the circumferential speed of air-flow is more than turntable locality peripheral linear speed, i.e., when the swirl ratio of air-flow is greater than 1, air-flow meeting again
By a radial coriolis force effect radially, which hinders the inside flowing of air-flow together with centrifugal force, such as Fig. 2 institute
Show, cause stress loss, to reduce bleed flow.
In the prior art, by derotation nozzle, subtract the structures such as scroll and long straight eddy plate to solve the problems, such as this, but all exist
Certain disadvantage, specific as follows:
1) principle of derotation nozzle is opposite with compressor disc chamber rotary speed direction by setting in bleed entrance and at one
The series of spray nozzles of constant inclination rake angle gives the air-flow of introducing certain reverse rotation speed, after air-flow enters disk chamber, relative to disk
As soon as chamber just has a relative velocity contrary with disk chamber locality linear velocity in the circumferential, in this way, air-flow will receive a diameter
It is used to inside Ge Shi masterpiece, this, to the loss of disk cavity pressure is reduced, is beneficial for increase bleed flow.However, a large amount of
Studies have shown that this derotation nozzle in practical application there are so-called hysterical effect, in transition state, work is not very
Stablize, the risk of jumping occurs there are flow, poor reliability, using few on Practical Project.
2) it is similar with the principle of long straight eddy plate to subtract scroll, i.e., in the intracavitary setting flow-guiding channel of disk, when disk chamber radial inward flow
Air-flow swirl ratio when will be greater than 1, air-flow is introduced into the channel design being fixed in disk chamber, pressure becomes air-flow swirl ratio
Close to 1, coriolis force radial in this way is largely reducing, this has also just reached reduction bleed drag losses, increases bleed flow
Purpose.This structure has application in engineering, but there is also some disadvantages, specifically includes that one, subtracts scroll and eddy plate
The problem of size is generally longer, easily causes vibration；Two, structure is complicated, and weight is relatively heavy, unfavorable to engine loss of weight；Three,
Installation fixed form is typically complex, and reliability is relatively poor.
Summary of the invention
To solve the above problems, this application provides a kind of short bendings applied to aero-engine compressor high position bleed
The position that the intracavitary swirl ratio of bleed air is greater than 1 is arranged in type eddy plate, the eddy plate, and eddy plate one end setting exists
The wall surface of the bleed air chamber, along compressorshaft to the intracavitary extension of bleed air, the eddy plate includes the other end
Close to compressor axis low radius parts and far from compressor axis high half path portion, the low radius parts include to
The curved structure in compressor direction of rotation.
Preferably, the wall surface of described eddy plate one end and the bleed air chamber is integrally designed.
Preferably, the preceding axle journal wall surface of described eddy plate one end and the bleed air chamber is integrally designed.
Preferably, the eddy plate centered on the intracavitary axis by compressor of bleed air circumferentially.
Preferably, the eddy plate is evenly equipped with 15-25 in the intracavitary circumferential direction of bleed air.
The present invention is reducing compressor disc chamber bleed resistance, can play obvious action in terms of increasing bleed flow.Due to
There is superior performance in terms of lightweight and reliability without installation using the short twisted plate structure of integration.
Detailed description of the invention
Fig. 1 is compressor disc chamber bleed schematic diagram.
Fig. 2 is no eddy plate structural schematic diagram.
Fig. 3 is the installation signal for the short flexure type eddy plate that the application is applied to the bleed of an aero-engine compressor high position
Figure.
Fig. 4 is the right view of embodiment illustrated in fig. 3.
Wherein, 1- sprue, air collecting chamber between 2- disk, 3- bleed slot, 4- bleed air chamber, 5- eddy plate, the low radius of 51-
Part, half path portion of 52- high, 6- rotary shaft.
Specific embodiment
To keep the purposes, technical schemes and advantages of the application implementation clearer, below in conjunction with the application embodiment
In attached drawing, the technical solution in the application embodiment is further described in more detail.In the accompanying drawings, identical from beginning to end
Or similar label indicates same or similar element or element with the same or similar functions.Described embodiment is
A part of embodiment of the application, rather than whole embodiments.Embodiment below with reference to attached drawing description is to show
Example property, it is intended to for explaining the application, and should not be understood as the limitation to the application.Based on the embodiment in the application,
Every other embodiment obtained by those of ordinary skill in the art without making creative efforts belongs to this
Apply for the range of protection.Presently filed embodiment is described in detail with reference to the accompanying drawing.
The present invention provides a kind of short flexure type eddy plate applied to aero-engine compressor high position bleed, such as Fig. 3
And shown in Fig. 4,4 inward eddy of bleed air chamber is arranged in than the position greater than 1 in the eddy plate 5, and described 5 one end of eddy plate is set
The wall surface in the bleed air chamber 4 is set, the other end extends along compressorshaft into bleed air chamber 4, described to subtract whirlpool
Plate 5 includes the low radius parts 51 close to compressor axis and high half path portion 52 far from compressor axis, and described low half
Path portion 51 includes to the curved structure in compressor direction of rotation.
The application in order to enable design subtract vortex structure preferably meets efficiently, lightweight, reliable requirement, numerical value can be passed through
The radial position determined where air-flow of the intracavitary swirl ratio of bleed air disk greater than 1 is emulated, flexure type is designed in the position and subtracts
The hardened structure in whirlpool is subtracting the most significant region arrangement eddy plate of whirlpool effect, rather than is arranging and subtract in the intracavitary extensive area of disk
Whirlpool plate is conducive to loss of weight in this way and reduces vibration.
Certain typical bleed air disk chamber is taken, such as Fig. 3 first carries out loopful Three-dimensional simulation without vortex structure is subtracted by disk chamber,
Obtaining relative velocity motion pattern, the intracavitary streamline of sighting disk, it is possible to find concentric structure is presented in the streamline in disk chamber at high radius,
The region swirl ratio is greater than 1, and occurs a large amount of discrete vortex structure in disk chamber at low radius, and the region swirl ratio is close to 1.It looks for
It is greater than 1 region to the intracavitary eddy flow of disk, high radius region as shown in Figure 3 measures region distribution in the radial direction, remembers
For range A.Eddy plate structure is set in disk chamber range A, through numerical simulation of optimum, the structure and circumferential direction of final selected eddy plate
Distribution as shown in figs. 3 and 4, is designed to flexure type at the low radius of eddy plate, curved direction is contrary with air-flow circumferential flow,
One and disk chamber rotation reversed opposite component velocity are obtained when air-flow can be made to flow through eddy plate in this way, to more effectively press down
The development of air-flow circumferential speed processed, has the function that further drag reduction.
The eddy plate is integrated with bearing block design, such as the eddy plate is integrally set with preceding axle journal wall surface in Fig. 3
Meter is fixed since eddy plate size is smaller without installing, can be by integration processing and manufacturing molding, this is to a certain extent
The reliability for subtracting vortex structure can be improved.
Numerical result shows to joined the eddy plate, and the air velocity of bleed slot outlet dramatically increases, bleed flow
Relative to without increasing 30% or more the case where subtracting vortex structure, this illustrates that the eddy plate rises in terms of increasing bleed air flow
Obvious action is arrived.
The present invention is reducing compressor disc chamber bleed resistance, can play obvious action in terms of increasing bleed flow.Due to
There is superior performance in terms of lightweight and reliability without installation using the short twisted plate structure of integration.
The above, the only specific embodiment of the application, but the protection scope of the application is not limited thereto, it is any
Within the technical scope of the present application, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
Cover within the scope of protection of this application.Therefore, the protection scope of the application should be with the scope of protection of the claims
It is quasi-.
Claims (5)
1. a kind of short flexure type eddy plate applied to aero-engine compressor high position bleed, which is characterized in that described to subtract whirlpool
In bleed air chamber (4) inward eddy than the position greater than 1, eddy plate (5) one end setting is calmed the anger described for plate (5) setting
The wall surface of power traction air cavity (4), the other end extend along compressorshaft into bleed air chamber (4), and the eddy plate (5) includes
Low radius parts (51) close to compressor axis and high half path portion (52) far from compressor axis, the low radius portion
Dividing (51) includes to the curved structure in compressor direction of rotation.
2. being applied to the short flexure type eddy plate of aero-engine compressor high position bleed, feature as described in claim 1
It is, the wall surface of described eddy plate (5) one end and the bleed air chamber (4) is integrally designed.
3. being applied to the short flexure type eddy plate of aero-engine compressor high position bleed, feature as claimed in claim 2
It is, the preceding axle journal wall surface of described eddy plate (5) one end and the bleed air chamber (4) is integrally designed.
4. being applied to the short flexure type eddy plate of aero-engine compressor high position bleed, feature as described in claim 1
Be, the eddy plate (5) in the bleed air chamber (4) centered on compressor axis circumferentially.
5. being applied to the short flexure type eddy plate of aero-engine compressor high position bleed, feature as described in claim 1
It is, the eddy plate (5) is evenly equipped with 15-25 in bleed air chamber (4) inner circumferential.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910690221.9A CN110454436B (en) | 2019-07-29 | 2019-07-29 | Short bending type vortex reducing plate applied to high-position air entraining of aero-engine compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910690221.9A CN110454436B (en) | 2019-07-29 | 2019-07-29 | Short bending type vortex reducing plate applied to high-position air entraining of aero-engine compressor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110454436A true CN110454436A (en) | 2019-11-15 |
| CN110454436B CN110454436B (en) | 2021-04-16 |
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| CN201910690221.9A Active CN110454436B (en) | 2019-07-29 | 2019-07-29 | Short bending type vortex reducing plate applied to high-position air entraining of aero-engine compressor |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113090593A (en) * | 2021-05-14 | 2021-07-09 | 中国航发湖南动力机械研究所 | Anti-rotation blade type vortex reduction air entraining structure suitable for turboshaft engine |
| CN113217120A (en) * | 2020-01-21 | 2021-08-06 | 中国航发商用航空发动机有限责任公司 | High-pressure turbine cooling air supply system and aircraft engine |
| CN118036342A (en) * | 2024-04-11 | 2024-05-14 | 中国航发四川燃气涡轮研究院 | Method for predicting temperature of air flow of disc center of air compressor based on test state |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113217120A (en) * | 2020-01-21 | 2021-08-06 | 中国航发商用航空发动机有限责任公司 | High-pressure turbine cooling air supply system and aircraft engine |
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| CN113090593A (en) * | 2021-05-14 | 2021-07-09 | 中国航发湖南动力机械研究所 | Anti-rotation blade type vortex reduction air entraining structure suitable for turboshaft engine |
| CN118036342A (en) * | 2024-04-11 | 2024-05-14 | 中国航发四川燃气涡轮研究院 | Method for predicting temperature of air flow of disc center of air compressor based on test state |
| CN118036342B (en) * | 2024-04-11 | 2024-06-18 | 中国航发四川燃气涡轮研究院 | Method for predicting temperature of air flow of disc center of air compressor based on test state |
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| CN110454436B (en) | 2021-04-16 |
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