CN202545354U - Casing treatment structure for compressor of aircraft engine - Google Patents
Casing treatment structure for compressor of aircraft engine Download PDFInfo
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- CN202545354U CN202545354U CN2012201226355U CN201220122635U CN202545354U CN 202545354 U CN202545354 U CN 202545354U CN 2012201226355 U CN2012201226355 U CN 2012201226355U CN 201220122635 U CN201220122635 U CN 201220122635U CN 202545354 U CN202545354 U CN 202545354U
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- treatment trough
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Abstract
The utility model relates to a casing treatment structure for a compressor of an aircraft engine, which comprises rotor blades and a casing shell, wherein arc gas treatment grooves are arranged on the inner side wall of the casing shell, adopt arc shapes inclining towards rotation directions of the rotor blades and comprise treatment groove upstream regions and treatment groove downstream regions, and openings of the treatment groove upstream regions and the treatment groove downstream regions have different circumferential opening degrees and radial inclined angles. The arc gas treatment grooves adopt arc shapes, internal flow of the treatment grooves is smoother, and loss caused by flow in treatment groove channels is reduced to the great extent. The casing treatment structure has the advantages that stable working margin is improved, the compressor efficiency is not sacrificed, and the casing treatment structure is simple and practical.
Description
Technical field
The utility model relates to a kind of processor casing structure that is used for aero-engine compressor, can realize the effect of fan/compressor stability-enhancement synergistic, is specially adapted to the high-performance aero gas turbine engine.
Background technique
In order to make the overall performance index of motor significantly improve, wherein most important means are to improve thrust weight ratio.This just has higher requirement to the design level of gas compressor/fan.Higher single-stage pressure ratio and efficient realize that on progression still less higher load just becomes the target that gas compressor, particularly fan development are pursued.Pursue higher level pressure ratio is the developing direction of various countries' development fan/compressor always.
Yet the load of fan/compressor level is high more, and is also harsh more to the requirement of its stable operation nargin condition, pursues higher level pressure ratio and improve between the gas compressor stable operation nargin existing certain contradiction.And as the gas turbine engine of present generation aircraft major impetus device; But requirement can keep stable work in wide flying speed scope and under various distortion and the unsettled inlet flow conditions; And the stable operation range of motor is by changes in flow rate scope decision possible between the operation point of fan/compressor and the stall border; If this scope is very little, stall margin is too small in other words, in case compression system gets into the astable mobile state of this type; To cause: (1) compressor performance extremely descends, so that is difficult to keep normal thermodynamic cycle process; (2) complete machine oscillation severe exacerbation very easily causes the fracture of gas compressor or turbine blade; (3) the high-temperature gas tempering in the firing chamber usually causes burning out gas compressor final stage stator blade; (4) hysteresis property of stall is having a strong impact on its releasing process again, even the stall phenomenon of in the F100 motor, removing because of intangibility has caused fatal crass's serious accident.This prevents the mobile unstable phenomenon of this type to take place with regard to forcing artificers must reserve enough stall margins; Yet; Typical case's gas compressor is efficient to close on the gas compressor unstability border of flowing usually with the high parameter operation area, and the way of the certain stall margin of this assurance is wasted concerning the performance of gas compressor beyond doubt greatly.Therefore hope that the stable operation range of gas compressor is wide more good more, so that gas compressor is being worked near efficient and high parameter operation area as far as possible.On the other hand, wideer stable operation range can allow motor off-design state farther, thereby makes motor that higher anti-distortion ability arranged and wideer flight envelope etc. is provided for aircraft.
Existing seam formula casing Processing Structure; Owing to having simple in structure, with low cost and need not to change expensive blade, remodeling is convenient, adds the reliability height; Expand surely effective; Characteristics such as anti-distortion ability is strong and being widely used in the actual model of many motors, like JT-9D motor, rice lattice 23 usefulness P-29 motors, Soviet Union's 27 usefulness Д Л-31 Ф motors ,-7 first motors are sprayed in meter lattice 29 usefulness P Д-33 motors and domestic whirlpool; Whirlpool spray-13; Whirlpool spray-14 motors etc., in the face of the not enough problem of stable operation nargin that is faced in the modern high load gas compressor design, casing is handled to have become and is used to one of important means that enlarges the gas compressor stable operation range in the world today.
Shown in Fig. 1-3, traditional axial slit formula processor box is the axially grooved of the gas compressor in the casing upper edge, radially the forming an angle of its groove depth direction and gas compressor.When the groove depth direction aimed at flow path direction, no matter incoming flow was equal uniform flow or the import distortion takes place, and stability margin all has bigger improvement.But the shortcoming of this type processor box is that the improvement of stability margin is a cost with the efficient of losing gas compressor.Why traditional processor box can reduce the peak efficiencies of gas compressor, one of them very important reasons be geometrical construction design unreasonable of treatment trough, not tissue treatment casing internal flow well.
Conventional axial seam rake joist processor casing structure utilized simultaneously pressure gradient and the blade path of Ye Ding both sides bigger flow to pressure gradient; Add the treatment trough conduit radially towards the blade sense of rotation several angle that tilted; Treatment trough is being played the part of the punching press effect; Make the blade path internal flow get into the treatment trough conduit, treatment trough is improved to the stable operation nargin that this pumping action at the blade path upper reaches makes.Yet this way makes the interior meeting of treatment trough produce stronger jet; Because the stronger jet of this strand has bigger circumferential speed component, and its direction is opposite with the blade sense of rotation, therefore; The jet that this strand is stronger is the main source of processor box flow losses; Its efficient to gas compressor has bigger influence: on the one hand, the circumferential speed that jet is quite high and and the inconsistency of main flow direction make that the blending between jet and the main flow is very strong, thereby bring higher loss; On the other hand, jet makes the leaf top incoming flow angle of attack increase, and has worsened leaf top inlet flow conditions, makes compressor efficiency obviously descend.
To disclose a kind of groove width be the asymmetric self-loopa processor box of parabolical centrifugal compressor and publication number is the one Chinese patent application of CN 101761511A; Though this scheme can improve the stable operation range of centrifugal-flow compressor; It is constant basically to keep efficient simultaneously; But have complex structure, problems such as manufacturing cost height are difficult on the real engine model, use.
The model utility content
The utility model technical problem to be solved provides a kind of reasonable in design, promptly having realized that stable operation nargin promotes does not sacrifice compressor efficiency, the simple and practical processor casing structure that is used for aero-engine compressor again.
It is this processor casing structure that is used for aero-engine compressor that the utility model solves the problems of the technologies described above the technological scheme that is adopted; Form by rotor blade and casing shell; Its structural feature is: described casing shell madial wall is provided with circular arc seam treatment trough; The semicircle camber design that said circular arc seam treatment trough adopts clockwise blades sense of rotation to tilt; Said circular arc seam treatment trough is divided into treatment trough upstream region, treatment trough downstream area, and said treatment trough upstream region has different circumferential openness and radial rake with the opening of treatment trough downstream area.Circular arc seam treatment trough adopts the design of semicircle camber, makes the treatment trough internal flow more smooth and easy, reduces the loss of flowing and producing in the treatment trough conduit as far as possible.
In order to take into account the stable operation nargin and the efficient of gas compressor, the number of the said circular arc seam of the utility model treatment trough is 6-8 a times of number of rotor blades.Treatment trough groove number is many more, and it is obvious more to expand steady effect, but can significantly reduce the efficient of gas compressor; And treatment trough groove number expands steady DeGrain at least.
In order to take into account the stable operation nargin and the efficient of gas compressor, the arc diameter of the said circular arc seam of the utility model treatment trough is that 60%～80% rotor blade leaf apical axis is to chord length.The steady effect of the big expansion of the diameter of circular arc is obvious, but loss is also bigger; The steady DeGrain of the expansion that arc diameter is little.
As preferably, the described treatment trough downstream area of the utility model covers the axial chord length scope of rotor blade Ye Ding upper reaches 30%-50%.
As preferably, the circumferential openness of the said treatment trough upstream region of the utility model is 30%～50%, and the openness of treatment trough downstream area is 50%～70%.Increase to the openness of the treatment trough opening of chord length covering the rotor Ye Ding upper reaches 30%～50% leaf apical axis, make blade path stream get into treatment trough more easily, increase the capacity of reflux in the treatment trough as far as possible, improve the steady ability of expansion of processor box;
As preferably, the described circular arc seam of the utility model treatment trough is 45～60 ° along the inclination angle
of rotor sense of rotation.
As preferably; The radial rake of the said treatment trough downstream area of the utility model opening
is 30 °～45 °, and the radial rake of treatment trough upstream region opening
is 60 °～80 °.
Suitably reduce the radial rake
of treatment trough opening; Make blade path stream get into treatment trough more easily; Increase the capacity of reflux in the treatment trough as far as possible, improve the steady ability of expansion of processor box.
The circumferential openness at treatment trough upstream open place is reduced; Suitably increase the radial rake
at groove downstream opening place simultaneously; Direction to jet on the basis that guarantees treatment trough geometrical construction integrity imposes appropriate control; Reduce the angle between it and the passage main flow as far as possible, weaken treatment trough to the negative effect of the jet of blade path to gas compressor.
The utility model is compared with existing technology and had the following advantages and effect: 1) treatment trough adopts the design of semicircle camber, makes the treatment trough internal flow more smooth and easy, reduces the loss of flowing and producing in the treatment trough conduit as far as possible; (2) will cover the rotor Ye Ding upper reaches 30%～50% leaf apical axis increases to the openness of the treatment trough opening of chord length; And suitably reduce the radial rake
of treatment trough opening; Make blade path stream get into treatment trough more easily; Increase the capacity of reflux in the treatment trough as far as possible, improve the steady ability of expansion of processor box; (3) the circumferential openness with treatment trough upstream open place reduces; Suitably increase the radial rake
at groove downstream opening place simultaneously; Direction to jet on the basis that guarantees treatment trough geometrical construction integrity imposes appropriate control; Reduce the angle between it and the passage main flow as far as possible, weaken treatment trough to the negative effect of the jet of blade path to gas compressor.
Description of drawings
Fig. 1 is traditional seam formula processor casing structure simplified schematic diagram.
Fig. 2 is that the A-A of Fig. 1 is to structural representation.
Fig. 3 is the meridian view of traditional seam formula processor box.
Fig. 4 is the structural representation sketch of the utility model.
Fig. 5 is that the A-A of Fig. 4 is to structural representation.
Fig. 6 is that the B-B of Fig. 4 is to structural representation.
Fig. 7 is that the C-C of Fig. 5 is to structural representation.
Label declaration: rotor blade 1, casing shell 2, circular arc seam treatment trough 3, treatment trough upstream region 4, treatment trough downstream area 5.
Embodiment
Below in conjunction with embodiment the utility model is done further detailed description, following examples are to the explanation of the utility model and the utility model is not limited to following examples.
Embodiment 1: shown in Fig. 4 to 7; Present embodiment is used for the processor casing structure of aero-engine compressor and is made up of rotor blade 1, casing shell 2; The madial wall of casing shell 2 is provided with circular arc seam treatment trough 3, and circular arc seam treatment trough 3 is divided into treatment trough upstream region 4,5 two parts of treatment trough downstream area.
In order to improve its stable operation nargin, on casing shell 2, having designed arc diameter is the semicircular arc seam formula circular arc seam treatment trough 3 of 60%～80% rotor blade, 1 leaf apical axis to chord length.The number of circular arc seam treatment trough 3 is 6～8 times of rotor blade 1 number; Circular arc seam treatment trough 3 has covered the rotor blade 1 Ye Ding upper reaches 30%～50% axial chord length scope; And the opening of treatment trough upstream region 4, treatment trough downstream area 5 has different openness (ratio that the area of circumferentially slotting is long-pending with casing shell 2 wall surfaces); Wherein the circumferential openness of treatment trough upstream region 4 is 30%～50%, and the openness of treatment trough downstream area 5 is 50%～70%.All circular arc seam treatment troughs 3 tilt 45 °～60 ° along compressor rotor blade 1 sense of rotation; And have different radial rakes along the rotor sense of rotation at treatment trough upstream region 4, treatment trough downstream area 5 openings; Wherein the radial rake of treatment trough downstream area 5 openings
is 30 °～45 °, and the radial rake of treatment trough upstream region 4 openings
is 60 °～80 °.
During work; The punching press effect of stitching treatment trough 3 by the pressure gradient in rotor blade 1 leaf top zone (pressure gradient of suction surface and pressure side both sides and rotor blade 1 passage bigger flow to pressure gradient) and circular arc; Make rotor blade 1 channel flow get into the conduit of circular arc seam treatment trough 3; Rotor blade 1 leaf top upstream region is produced pumping action, thereby improve the stable operation range of gas compressor.In addition, the direction of jet is imposed appropriate control, slacken circular arc seam treatment trough 3 to the negative effect of the jet of blade path to gas compressor through optimization process case structure parameter.
In sum, the utility model can directly be used for aviation gas turbine and start fan/machine gas compressor, in the stable operation nargin that increases substantially fan/machine gas compressor, improves the efficient of gas compressor.
The thinking of the utility model is the geometrical construction from the optimization process groove; Design the less processor box of flow losses in a kind of treatment trough; Broken " casing is handled and can be enlarged gas compressor stable operation nargin; but to lower efficiency " traditional concept, become the original intention of the said work of the utility model.
In addition, need to prove, the specific embodiment described in this specification, its zero, the shape of parts, institute's title of being named etc. can be different.Allly conceive equivalence or the simple change that described structure, characteristic and principle are done, include in the protection domain of the utility model patent according to the utility model patent.The utility model person of ordinary skill in the field can make various modifications or replenishes or adopt similar mode to substitute described specific embodiment; Only otherwise depart from the structure of the utility model or surmount the defined scope of these claims, all should belong to the protection domain of the utility model.
Claims (7)
1. processor casing structure that is used for aero-engine compressor; Form by rotor blade and casing shell; It is characterized in that: described casing shell madial wall is provided with circular arc seam treatment trough; The semicircle camber design that said circular arc seam treatment trough adopts clockwise blades sense of rotation to tilt; Said circular arc seam treatment trough is divided into treatment trough upstream region, treatment trough downstream area, and said treatment trough upstream region has different circumferential openness and radial rake with the opening of treatment trough downstream area.
2. the processor casing structure that is used for aero-engine compressor according to claim 1 is characterized in that: the number of said circular arc seam treatment trough is 6-8 a times of number of rotor blades.
3. the processor casing structure that is used for aero-engine compressor according to claim 1 and 2 is characterized in that: the arc diameter of said circular arc seam treatment trough is that 60%～80% rotor blade leaf apical axis is to chord length.
4. the processor casing structure that is used for aero-engine compressor according to claim 3 is characterized in that: described treatment trough downstream area covers the axial chord length scope of rotor blade Ye Ding upper reaches 30%-50%.
5. the processor casing structure that is used for aero-engine compressor according to claim 4 is characterized in that: the circumferential openness of said treatment trough upstream region is 30%～50%, and the openness of treatment trough downstream area is 50%～70%.
6. the processor casing structure that is used for aero-engine compressor according to claim 4 is characterized in that: described circular arc seam treatment trough is 45～60 ° along the inclination angle of rotor sense of rotation.
7. the processor casing structure that is used for aero-engine compressor according to claim 4; It is characterized in that: the radial rake of said treatment trough downstream area opening
is 30 °～45 °, and the radial rake of treatment trough upstream region opening
is 60 °～80 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012201226355U CN202545354U (en) | 2012-03-28 | 2012-03-28 | Casing treatment structure for compressor of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012201226355U CN202545354U (en) | 2012-03-28 | 2012-03-28 | Casing treatment structure for compressor of aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202545354U true CN202545354U (en) | 2012-11-21 |
Family
ID=47165996
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012201226355U Expired - Lifetime CN202545354U (en) | 2012-03-28 | 2012-03-28 | Casing treatment structure for compressor of aircraft engine |
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| CN (1) | CN202545354U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102606529A (en) * | 2012-03-28 | 2012-07-25 | 杭州诺沃能源科技有限公司 | Processing case structure for gas compressor of aircraft engine |
-
2012
- 2012-03-28 CN CN2012201226355U patent/CN202545354U/en not_active Expired - Lifetime
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102606529A (en) * | 2012-03-28 | 2012-07-25 | 杭州诺沃能源科技有限公司 | Processing case structure for gas compressor of aircraft engine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| ASS | Succession or assignment of patent right |
Owner name: XECA TURBO TECHNOLOGIES (BEIJING) TECHNOLOGY CO., Free format text: FORMER OWNER: HANGZHOU NUOVO POWER ENGINEERING CO., LTD. Effective date: 20141105 |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| COR | Change of bibliographic data |
Free format text: CORRECT: ADDRESS; FROM: 310014 HANGZHOU, ZHEJIANG PROVINCE TO: 100107 CHAOYANG, BEIJING |
|
| TR01 | Transfer of patent right |
Effective date of registration: 20141105 Address after: 100107 A block, Tianlong garden, Beijing, Chaoyang District Patentee after: Potential plus (Beijing) Technology Co., Ltd. Address before: Hangzhou City, Zhejiang province 310014 City Road No. 588 7 Fei Jia Tang room 313 (address:214 rooms) Patentee before: Hangzhou Nuovo Power Engineering Co., Ltd. |
|
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20121121 |