CN106382260A - Gas compressor chordwise groove flow guiding sheet type casing treatment method and device - Google Patents
Gas compressor chordwise groove flow guiding sheet type casing treatment method and device Download PDFInfo
- Publication number
- CN106382260A CN106382260A CN201610895513.2A CN201610895513A CN106382260A CN 106382260 A CN106382260 A CN 106382260A CN 201610895513 A CN201610895513 A CN 201610895513A CN 106382260 A CN106382260 A CN 106382260A
- Authority
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- China
- Prior art keywords
- groove
- blade
- leaf
- gas compressor
- water conservancy
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- 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
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/522—Casings; Connections of working fluid for axial pumps 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
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
-
- 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
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
- F04D29/544—Blade shapes
Abstract
The invention discloses a gas compressor chordwise groove flow guiding sheet type casing treatment method and device. A plurality of blade top chordwise grooves are formed in the wall face of a gas compressor casing in the circumferential direction, and the groove depth direction is consistent with the radial direction of a gas compressor. Then, a plurality of flow guiding blades are arranged in the grooves in the blade top chordwise direction. A blade channel composed of every two adjacent flow guiding blades is a shrinkage channel. When the blades are located below the grooves every time, the low-energy leakage flow near the blade top pressure faces can be sucked into the grooves under the action of the pressure difference between the blade top pressure faces and suction faces, after airflow is accelerated in the shrinkage runners through the flow guiding blades in the grooves, the airflow enters the blade channels again in the direction close to mainstream from the position near the suction faces, and the leakage flow and blade surface boundary layers can be simulated as well. According to the chordwise groove flow guiding sheet type casing treatment method, flowing blockage in the blade top areas can be effectively relieved, and accordingly the function of enlarging the stable work range of the gas compressor is achieved.
Description
Technical field
The present invention relates to a kind of treated casing method and device, more particularly, to a kind of tangential groove water conservancy diversion chip treated casing
Flow control method and device, for improving the stable operation range of axial flow compressor, belong to turbomachine field.
Background technology
Axial flow compressor is one of core component of aero-engine, with aero-engine to high thrust-weight ratio, low-fuel-comsuption
Rate and high stability direction are developed, and the stable operation range making it have broadness while improving compressor load and efficiency is to grind
Study carefully the target that personnel persistently pursue.When the flow that the rotating speed of compressor necessarily passes through compressor reduces to a certain extent, pressure
The flow instabilities phenomenon such as rotating stall occurs in mechanism of qi, compressor blade fracture and engine misses when serious, can be caused.
Compressor operatlng polnt is generally described with stall margin apart from the safe coefficient of instability boundary.Compressor rotating stall etc. flows
Unstable phenomenon limits the stable operation range of aero-engine.
Compressor rotating stall show as single or multiple low speed flow areas with certain rotating speed along rotor direction of rotation
Rotate.See fastening with rotary speed of rotator identical relative coordinates, stall zone is along the direction contrary with rotor direction of rotation
Propagate.Fasten in static absolute coordinate and see, stall zone is propagated along with rotor direction of rotation identical direction, and stall zone
Rotating speed will be less than the rotating speed of rotor.The rotating stall of compressor generally comes across Ye Ding region, high load capacity gas compressor blade top at first
There is the complicated interaction between intense shock wave, leakage vortex and boundary region in region, easily the larger flowing blocking of induction.Compressor
The flowing blocking in Ye Ding region is the major reason causing rotating stall, constrains the stall margin of compressor.In order to improve pressure
The stall margin of mechanism of qi, can be using flow control methods such as treated casing, the micro- jet in leaf top and variable inlet guide vanes.At casing
Reason can effectively improve the stable operation range of compressor as a kind of passive flow control method, and reliability is higher and is tying
It is relatively easy on structure realize.Treated casing technology has obtained the application of reality in aero-engine at present.
The flowing that treated casing can improve gas compressor blade top region by changing the geometry of leaf top casing blocks shape
Condition, thus play the effect widening compressor stall nargin.The flowing in gas compressor blade top region is extremely complex three-dimensional in itself
Flowing, and the interaction between treated casing and leaf overhead stream field aggravates its complexity.How to design treated casing structure
Effectively improve compressor stable operation range, reduce the loss in efficiency of compressor simultaneously as far as possible, be still current turbomachine neck
The challenging problem in domain.
Content of the invention
It is an object of the invention to provide a kind of compressor tangential groove water conservancy diversion chip treated casing flow control method and
Device, is effectively transported to gas compressor blade overhead stream body and is encouraged, thus reducing blade-tip leakage flow and boundary layer separation causes
Blocking, improve compressor stall margin.
The technical solution that the present invention is adopted by its technical problem of solution is：
A kind of compressor tangential groove water conservancy diversion chip treated casing flow control method, it is characterised in that：At described casing
Reason flow control method comprises the steps,
SS1. open up some being uniformly distributed circumferentially in gas compressor moving blade top corresponding compressor processor box wall
To groove, the direction of groove depth has certain gap along the radial direction of compressor, each leaf top chord between groove to leaf top chord；
SS2. in each leaf top chord to inside grooves along leaf top chord to being evenly arranged several guide vanes, in guide recess
The trend of air-flow, adjacent guide vanes constitute blade path along leaf pressure on top surface face direction arrive suction surface direction be convergent passage,
After near leaf pressure on top surface face, entrance leaf top chord accelerates in convergent passage to the leakage stream in groove near the suction surface of leaf top
Enter blade path along close to main flow direction, the energy of leaf top regional fluid can be increased, thus realize to blade-tip leakage flow and
The detached control of leaf table boundary layer, makes the flowing in Ye Ding region block and mitigates, the stall margin of compressor improves.
Preferably, described leaf top chord is the 0.5-1.0 to chord length for the gas compressor moving blade leaf apical axis to the axial length of groove
Times.
Preferably, described leaf top chord is 0.1-0.5 times to chord length of gas compressor moving blade leaf apical axis to the width of groove.
Preferably, described leaf top chord is 0.1-0.5 times to chord length of gas compressor moving blade leaf apical axis to the depth of groove.
Preferably, described leaf top chord is 1-50 to the number of groove.
Preferably, the established angle of described guide vane is 0-90 degree.
Preferably, the import geometry angle of described guide vane is 0-90 degree.
Preferably, the outlet geometry angle of described guide vane is 0-45 degree.
Preferably, the chord length of described guide vane is 0.1-0.9 times to chord length of gas compressor moving blade leaf apical axis.
Preferably, the height of described guide vane is 0.1-0.9 times to depth of groove of leaf top chord.
Preferably, the maximum gauge of described guide vane is 0.05-0.10 times of guide vane chord length.
Preferably, single leaf top chord is 1-10 to the number of groove Inner guide blade.
Preferably, the blade path shrinkage ratio of adjacent guide vanes composition is 0.1-0.9.
According to a further aspect in the invention, additionally provide a kind of flowing control of compressor tangential groove water conservancy diversion chip treated casing
Device processed, including gas compressor moving blade and compressor casing it is characterised in that
Described gas compressor moving blade top corresponding compressor processor box wall opens up some being uniformly distributed circumferentially
Leaf top chord to groove, groove depth direction from described leaf top chord to groove along compressor radial direction, each leaf top chord is to groove
Between there is certain gap；In each described leaf top chord to inside grooves along leaf top chord to being evenly arranged several water conservancy diversion leaves
Piece, the blade path that adjacent guide vanes are constituted is formed as convergent passage along leaf pressure on top surface face direction to suction surface direction, from leaf
After near pressure on top surface face, entrance leaf top chord accelerates in convergent passage to the leakage stream in groove, near the suction surface of leaf top, edge connects
It is bordering on main flow direction and enters blade path, the energy of leaf top regional fluid can be increased, thus realizing to blade-tip leakage flow and Ye Biao
The control of boundary layer separation, makes the flowing in Ye Ding region block and mitigates, the stall margin of compressor improves.
Compared with the existing technology, the tangential groove water conservancy diversion chip treated casing steady for compressor expansion proposed by the invention
Method and device, its advantage is：
The distribution in leakage intensity of flow and direction, leaf in this treated casing structure controllable part or the long scope of whole leaf top chord
Top chord can absorb the mental retardation leakage stream near leaf pressure on top surface face to groove when being located above leaf top such that it is able to suppression leaf top is let out
Being formed and weaken the pressure face low regime that nearby leakage stream causes of leakage current；Guide vane in groove can make entrance recessed simultaneously
Air-flow in groove accelerates in the convergent passage that adjacent guide vanes form, and guides air-flow along the direction close to main flow from suction
Power injects blade path near face, plays incentive action to mental retardation leakage stream and blade suction surface boundary region such that it is able to reduce
The flowing blocking in Ye Ding region, reaches the purpose improving compressor stable operation range.
Brief description
Fig. 1 is the meridian plane structure of the compressor tangential groove water conservancy diversion chip treated casing flow control apparatus of the present invention
Figure.
Fig. 2 is the Section A-A structure chart in Fig. 1.
Fig. 3 is the section B-B structure chart in Fig. 1.
Specific embodiment
For making the objects, technical solutions and advantages of the present invention become more apparent, develop simultaneously embodiment referring to the drawings, right
The present invention further describes.It should be noted that described below is only presently preferred embodiments of the present invention, therefore do not limit
Determine protection scope of the present invention.
It should be noted that the implementation not illustrating in accompanying drawing or describing, it is ordinary skill people in art
Form known to member.Additionally, the direction term mentioned in following examples, for example " on ", D score, "front", "rear", " left ",
" right ", " top ", " bottom " etc., are only the directions of refer to the attached drawing.Therefore, the direction term of use is used to explanation not for limiting
The present invention.
Below in conjunction with the accompanying drawings and by specific embodiment the objects, technical solutions and advantages of the present invention are carried out specifically
Bright.
Fig. 1 is the meridian plane structure of the compressor tangential groove water conservancy diversion chip treated casing flow control apparatus of the present invention
Figure.The compressor tangential groove water conservancy diversion chip treated casing flow control apparatus of the present invention include：Gas compressor moving blade 1, compressor
Casing 2, leaf top chord is to the guide vane 4 of groove 3 and inside grooves.Exist certain between gas compressor moving blade 1 and compressor casing 2
Blade tip clearance.In the presence of pressure reduction between leaf pressure on top surface face and suction surface, air-flow forms leakage stream through blade tip clearance, lets out
Leakage current is the major reason causing compressor rotating stall.In corresponding compressor casing 2 wall in gas compressor moving blade 1 leaf top circumferentially
Direction opens up multiple leaf top chords to groove 3, and is evenly arranged multiple inside each leaf top chord is to groove 3 along leaf top chord length direction
Guide vane 4, can improve the flow field in Ye Ding region, thus reaching the purpose improving compressor stable operation range.
Described leaf top chord covers 0%-100% gas compressor moving blade leaf apical axis to chord length scope to groove 3；Leaf top chord is to groove
Depth LhFor its axial length Lt33.3%；The height D of guide vanehFor leaf top chord to depth of groove Lh90%.
Fig. 2 is the Section A-A structure chart in Fig. 1.At least corresponding 1 leaf top chord of each gas compressor moving blade 1 is to groove 3；Leaf
Top chord is consistent with the radial direction of compressor to the groove depth direction of groove 3；Leaf top chord is its axial length to the width of groove
25%.
Fig. 3 is the section B-B structure chart in Fig. 1.It is arranged on each leaf top chord to the quantity of the guide vane 4 in groove 3
For 4；The import geometry angle beta of guide vane 41=60 degree；The outlet geometry angle beta of guide vane 42=20 degree；Guide vane 4
Established angle ε=40 degree；The chord length of guide vane 4 is leaf apical axis to chord length 50%；The blade profile maximum gauge of guide vane 4 is to lead
The 10% of stream blade chord length；The blade path of adjacent guide vanes 4 composition is to shrink passage, the shrinkage ratio of guide vane passage
w2/w1=0.5.
The gas compressor moving blade 1 of rotation and leaf top chord become in time to the relative position between groove 3 and guide vane 4
Change.When gas compressor moving blade 1 is located at leaf top chord to groove 3 and guide vane 4 lower section, guide vane 4 is across gas compressor moving blade 1
Top.In the presence of pressure reduction between leaf pressure on top surface face and suction surface, the mental retardation leakage stream near leaf pressure on top surface face can enter
Into groove 3, this can make to reduce by the leakage intensity of flow of blade tip clearance leaf top chord.Meanwhile, enter leaf top chord into groove 3
Subsonics air-flow ramps up in the contraction passage that adjacent guide vanes 4 form, and in the presence of guide vane 4 along close to
The direction of main flow enters blade path near the suction surface of leaf top, can play excitation to blade-tip leakage flow and suction surface boundary region
Effect.Therefore, tangential groove guide vane formula treated casing flow control apparatus can reduce the flowing blocking in Ye Ding region, carries
The stable operation range of high pressure mechanism of qi.
Leaf top chord needs to be carried out according to specific application to the number of groove 3 and guide vane 4 and geometric parameter
Choose and optimize, more effectively to improve the stall margin of compressor, and reduce efficiency and the pressure ratio loss of compressor as far as possible.
The foregoing is only presently preferred embodiments of the present invention, not in order to limit the present invention, all essences in the present invention
Within god and principle, any modification, equivalent substitution and improvement done etc., should be included within the scope of the present invention.
Claims (10)
1. a kind of compressor tangential groove water conservancy diversion chip treated casing flow control method it is characterised in that：Described flowing controls
Method includes：
SS1. some leaves being uniformly distributed circumferentially are opened up on the corresponding compressor processor box wall of gas compressor moving blade top
To groove, the direction of groove depth has certain gap along the radial direction of compressor, adjacent leaf top chord between groove to top chord；
SS2. in each leaf top chord to inside grooves along leaf top chord to being evenly arranged several guide vanes, adjacent two guide vanes
Constitute convergent passage, enter near leaf pressure on top surface face after leaf top chord accelerates to the leakage stream in groove in convergent passage from leaf
Top suction surface nearby enters blade path along close to main flow direction, can increase the energy of leaf top regional fluid, thus realize right
Blade-tip leakage flow and the detached control of leaf table boundary layer, make the flowing in Ye Ding region block and mitigate, the stall margin of compressor carries
High.
2. the tangential groove water conservancy diversion chip treated casing method according to the claims it is characterised in that：Described leaf
Top chord is 0.5-1.0 times to chord length of gas compressor moving blade leaf apical axis to the axial length of groove.
3. the tangential groove water conservancy diversion chip treated casing method according to the claims it is characterised in that：Described leaf
Top chord is 0.1-0.5 times to chord length of gas compressor moving blade leaf apical axis to the width of groove.
4. the tangential groove water conservancy diversion chip treated casing method according to the claims it is characterised in that：Described leaf
Top chord is 0.1-0.5 times to chord length of gas compressor moving blade leaf apical axis to the depth of groove.
5. the tangential groove water conservancy diversion chip treated casing method according to the claims it is characterised in that：Described leaf
Top chord is 1-50 to the number of groove.
6. the tangential groove water conservancy diversion chip treated casing method according to the claims it is characterised in that：Described leads
The established angle of stream blade is 0-90 degree.
7. the tangential groove water conservancy diversion chip treated casing method according to the claims it is characterised in that：Described leads
The import geometry angle of stream blade is 0-90 degree.
8. the tangential groove water conservancy diversion chip treated casing method according to the claims it is characterised in that：Described leads
The outlet geometry angle of stream blade is 0-45 degree.
9. the tangential groove water conservancy diversion chip treated casing method according to the claims it is characterised in that：Described leads
The chord length of stream blade is 0.1-0.9 times to chord length of gas compressor moving blade leaf apical axis.
10. the tangential groove water conservancy diversion chip treated casing method according to the claims it is characterised in that：Described leads
The height of stream blade is 0.1-0.9 times to depth of groove of leaf top chord.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610895513.2A CN106382260B (en) | 2016-10-14 | 2016-10-14 | A kind of tangential groove water conservancy diversion chip treated casing method and device of compressor |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610895513.2A CN106382260B (en) | 2016-10-14 | 2016-10-14 | A kind of tangential groove water conservancy diversion chip treated casing method and device of compressor |
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| Publication Number | Publication Date |
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| CN106382260A true CN106382260A (en) | 2017-02-08 |
| CN106382260B CN106382260B (en) | 2018-08-10 |
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| CN201610895513.2A Active CN106382260B (en) | 2016-10-14 | 2016-10-14 | A kind of tangential groove water conservancy diversion chip treated casing method and device of compressor |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106837879A (en) * | 2017-03-31 | 2017-06-13 | 浙江理工大学 | A kind of compressor case and its backflow bootstrap technique with arc-shaped slit |
| CN110094364A (en) * | 2018-01-31 | 2019-08-06 | 中国航发商用航空发动机有限责任公司 | A kind of rotor blade and axial flow compressor |
| CN113883095A (en) * | 2021-11-02 | 2022-01-04 | 北京航空航天大学 | Casing and fluid power equipment |
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| US4871294A (en) * | 1982-06-29 | 1989-10-03 | Ivanov Sergei K | Axial-flow fan |
| JPH08232605A (en) * | 1994-12-29 | 1996-09-10 | United Technol Corp <Utc> | Chip shroud assembly for axial-flow gas-turbine engine |
| CN1420285A (en) * | 2001-11-15 | 2003-05-28 | 北京新安特玻璃钢设备有限公司 | Positive- and negative-direction blowing-in and-out stilling -eliminating fan |
| CN1646790A (en) * | 2002-02-28 | 2005-07-27 | Mtu飞机发动机有限公司 | Recirculation structure for turbo chargers |
| CN101092977A (en) * | 2007-07-23 | 2007-12-26 | 北京航空航天大学 | Method for designing box of processor |
| CN202149080U (en) * | 2011-07-21 | 2012-02-22 | 浙江义乌星耀风机有限公司 | Coal gas axial flow fan provided with performance stabilizer |
| CN103062131A (en) * | 2011-10-20 | 2013-04-24 | 中国科学院工程热物理研究所 | Flexible non-axisymmetric processing flow control method of casing |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4871294A (en) * | 1982-06-29 | 1989-10-03 | Ivanov Sergei K | Axial-flow fan |
| JPH08232605A (en) * | 1994-12-29 | 1996-09-10 | United Technol Corp <Utc> | Chip shroud assembly for axial-flow gas-turbine engine |
| CN1420285A (en) * | 2001-11-15 | 2003-05-28 | 北京新安特玻璃钢设备有限公司 | Positive- and negative-direction blowing-in and-out stilling -eliminating fan |
| CN1646790A (en) * | 2002-02-28 | 2005-07-27 | Mtu飞机发动机有限公司 | Recirculation structure for turbo chargers |
| CN101092977A (en) * | 2007-07-23 | 2007-12-26 | 北京航空航天大学 | Method for designing box of processor |
| CN202149080U (en) * | 2011-07-21 | 2012-02-22 | 浙江义乌星耀风机有限公司 | Coal gas axial flow fan provided with performance stabilizer |
| CN103062131A (en) * | 2011-10-20 | 2013-04-24 | 中国科学院工程热物理研究所 | Flexible non-axisymmetric processing flow control method of casing |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106837879A (en) * | 2017-03-31 | 2017-06-13 | 浙江理工大学 | A kind of compressor case and its backflow bootstrap technique with arc-shaped slit |
| CN110094364A (en) * | 2018-01-31 | 2019-08-06 | 中国航发商用航空发动机有限责任公司 | A kind of rotor blade and axial flow compressor |
| CN113883095A (en) * | 2021-11-02 | 2022-01-04 | 北京航空航天大学 | Casing and fluid power equipment |
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| Publication number | Publication date |
|---|---|
| CN106382260B (en) | 2018-08-10 |
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