CN202220756U - Adsorption type compressor stator blade - Google Patents
Adsorption type compressor stator blade Download PDFInfo
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- CN202220756U CN202220756U CN201120327190XU CN201120327190U CN202220756U CN 202220756 U CN202220756 U CN 202220756U CN 201120327190X U CN201120327190X U CN 201120327190XU CN 201120327190 U CN201120327190 U CN 201120327190U CN 202220756 U CN202220756 U CN 202220756U
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- 238000001179 sorption measurement Methods 0.000 title claims abstract description 36
- 230000003068 static effect Effects 0.000 claims abstract description 83
- 238000012360 testing method Methods 0.000 description 8
- 230000000694 effects Effects 0.000 description 4
- 238000011160 research Methods 0.000 description 4
- 238000009530 blood pressure measurement Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000007664 blowing Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000005086 pumping Methods 0.000 description 2
- 238000002604 ultrasonography Methods 0.000 description 2
- 238000012795 verification Methods 0.000 description 2
- 241000233855 Orchidaceae Species 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000007667 floating Methods 0.000 description 1
- 238000005247 gettering Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000013022 venting Methods 0.000 description 1
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Abstract
An adsorption type compressor stator blade. The suction surface of the blade body is provided with a plurality of suction holes and a plurality of static pressure holes. The suction holes are uniformly arranged from the front edge to the rear edge of the blade body. The number of the static pressure holes is the same as the row number of the suction holes. The static pressure holes are distributed in a row from the front edge of the blade body to the rear edge and are positioned between the suction hole and the blade root or the blade tip. The blade body is internally provided with a vacuum cavity and a static pressure cavity which are communicated with the blade crown. The number of the vacuum cavities is the same as the row number of the suction holes, and the number of the static pressure cavities is the same as the number of the static pressure holes. Each vacuum cavity inside the blade body is communicated with the blade shroud, so that the suction gas on the surface of the blade body enters the vacuum cavities and is discharged through the blade shroud; each static pressure cavity in the blade body is communicated with the blade shroud, so that the static pressure holes are communicated with the static pressure cavities in the blade body, the static pressure is transmitted to the outside of the compressor through the blade shroud, and the change of the static pressure on the surface of the blade before and after suction is measured through the static pressure holes, so that the influence of suction of the boundary layer on the surface of the blade on the performance of the compressor is determined.
Description
Technical field
The present invention relates to the gas compressor field, specifically is a kind of adsorption type compressor blade.
Background technique
The modern high performance development of Aeroengines requires its critical component gas compressor to have higher pressure ratio and efficient.It is one of method that improves gas compressor pressure ratio and load that thereby raising compressor blade row bent angle adds the deflection angle of air flow in compressor blade row, often is attended by the boundary layer separation but increase bent angle, makes compressor efficiency and negotiability decline to a great extent.
1997, professor Kerrebrock proposed adsorption type gas compressor notion first, and pointing out can increase air-flow turn back ability and negotiability through blade surface boundary layer suction, and can improve compressor efficiency.In recent years, NASA Green cooperates with the Massachusetts Institute of Technology in the research center, has launched series of studies work to adsorption type gas compressor technology, has developed adsorption type gas compressor testpieces, and has carried out verification experimental verification.See from the documents and materials of its announcement; The adsorption type gas compressor of NASA Green research center and Massachusetts Institute of Technology's design is all opened single groove at each blade suction surface along leaf exhibition direction and is carried out the boundary layer suction; Along the venting of stator wheel hub, to improve the load and the efficient of gas compressor.
The domestic Chinese Academy of Sciences, Harbin Institute of Technology, Nanjing Aero-Space University, China Gas Turbine Research Inst. etc. carry out excessive quantity research aspect the adsorption type gas compressor.Research points out that boundary layer suction port position and gettering quantity have considerable influence to adsorption type gas compressor performance.The Niu Yuchuan of the Chinese Academy of Sciences has introduced a kind of adsorption type compressor blade row in its master thesis " experimental study of adsorption type compressor blade row and analysis "; This adsorption type leaf grating cracks along full leaf height; Stitch wide 1mm; Laying external diameter in the air-breathing groove is the plastic tube of 2mm for the 3mm internal diameter, and leaf grating is bled.The paper that Nanjing Aero-Space University, China Gas Turbine Research Inst. orchid be prosper, visit person of outstanding talent, Liang Dewang, yellow state equality week " stride, the test of ultrasound velocity adsorption type gas compressor plane cascade " has been introduced and has a kind ofly been striden, ultrasound velocity adsorption type gas compressor plane cascade.This compressor blade row cracks along the high direction of leaf blade suction surface is aspirated.The introduction that the patent of invention " blowing or the sucking type air compressor cascade pilot system " of old floating, the Song Yanping of Harbin Institute of Technology, Chen Shaowen, Lu Huawei etc. is more detailed a kind of air blowing or sucking type air compressor cascade pilot system; Blade in this system is a hollow blade, realizes the boundary layer suction for open single groove along the high direction of leaf.
Above-mentioned adsorption type compressor blade/leaf grating is all opened single groove along the high direction of leaf and is carried out air-breathingly, improves compressor efficiency through boundary layer suction.But different compressor blades has different best suction location; Same blade suction location under different operating modes also is not quite similar; Said apparatus need be processed many group blade/leaf gratings and test, and can't obtain best suction location through same group of blade, and process of the test is numerous and diverse; The adsorption type gas compressor of NASA Green research center and Massachusetts Institute of Technology's development is all slotted on each blade, and required pumping equipment power is bigger, and capital is more.
Summary of the invention
Bleed for overcoming the single suction bole that passes through that exists in the existing technology; Need the many groups of processing adsorption type compressor blade/leaf grating, carry out the test of many group adsorption type gas compressors; And the adsorption type gas compressor is all slotted on each stator blade; Required pumping equipment power is bigger, and the deficiency that capital is more the present invention proposes a kind of adsorption type gas compressor stator blade.
The present invention includes blade and integral shroud.There is fixing pin at the place at blade tip.The suction surface of blade is placed with a plurality of suction boles and a plurality of baroport.Said suction bole is evenly distributed between leading edge to the trailing edge of blade, and the distance of centre distance blade inlet edge of first row's suction bole is 10～50% chord lengths, and distance of the centre distance trailing edge of last row's suction bole is 10～28% chord lengths.The first row suction bole is that 5～50% leaves are high apart from the distance of blade tip, and last row suction bole is that 45～95% leaves are high apart from the distance of blade tip.The aperture of suction bole is 1.2～2mm.
The quantity of said baroport is identical with row's number of suction bole.Each baroport becomes a column distribution from the leading edge place of blade to the trailing edge place, and between suction bole and blade root or blade tip.The same chordwise location that is centered close to of suction bole is arranged at the center of each baroport respectively with each; Distance between the center of baroport and the center of adjacent suction bole is 2～5mm.
There is vacuum chamber and the static pressure chamber that connects with integral shroud the inside of blade.Wherein, the quantity of vacuum chamber is identical with row's number of suction bole.Each vacuum chamber is corresponding with the position of each row's suction bole in the tangential position of stator blade.The center of each vacuum chamber all is positioned on the center line of blade root place blade profile.The center line of said vacuum chamber is vertical each other with the center line of suction bole.One end of each vacuum chamber connects integral shroud, the other end respectively with row's suction bole in the hole dolly in each hole direct-connected logical.The quantity in said static pressure chamber is identical with the number of baroport.The center line in static pressure chamber is vertical each other with the center line of baroport; Described each static pressure chamber is corresponding with the position of each row's baroport respectively in the tangential position of blade.Distance between the center in the center of vacuum chamber and static pressure chamber is 3～4mm.Each static pressure chamber is the high direction of the leaf along blade from the blade root end face, extends to the blade tip place, and direct-connected logical with respectively with the hole dolly of row's baroport.There is the through hole that is communicated with inner each vacuum chamber of blade and each static pressure chamber on the surface of integral shroud.
Fixing pin is positioned at the blade tip end of blade.The center of fixing pin overlaps with the center line in blade tip cross section, and is positioned at 30～70% chord length places in blade tip cross section.
The diameter of baroport is 0.8～1.5mm; The vacuum chamber diameter is 2mm, and static pressure chamber diameter is 1mm.Fixing pin end face middle part has the groove that is connected with the gas compressor wheel hub; Described groove is along the tangential horizontal distribution of blade.
When baroport was between blade root and suction bole, the static pressure chamber was between vacuum chamber and blade suction surface; When baroport was between blade tip and suction bole, the static pressure chamber was between vacuum chamber and blade pressure surface.
Each inner vacuum chamber of blade of the present invention all connects with integral shroud, make the surperficial intake-gas entering vacuum chamber of blade after, discharge through integral shroud; Each inner static pressure chamber of blade all connects with integral shroud; Baroport is communicated with the inner static pressure chamber of blade; Through integral shroud static pressure is reached the gas compressor outside; Measure the variation of static pressure before and after suction of blade surface through baroport, to confirm that the suction of blade surface boundary layer is to the gas compressor Effect on Performance.
The present invention installs the gas compressor stator blade of one or more a kind of suction surface suctions on the gas compressor stator, only can realize the adsorption type gas compressor test of multi-operating mode, different suction position with a cover adsorption type gas compressor stator.Static pressure through measuring in the baroport changes before and after suction, obtains different suction position and suction flow to the gas compressor influence on flow field, searches out best suction position and suction flow under each operating mode.The present invention is simple and direct, realized the suction of gas compressor stator blade boundary layer effectively, and can significantly practice thrift experimentation cost.
Description of drawings
Fig. 1 is the 3-D view of adsorption type gas compressor stator blade;
Fig. 2 is the plan view of adsorption type gas compressor stator blade;
Fig. 3 is the plan view of adsorption type gas compressor stator blade;
Fig. 4 is the left view of adsorption type gas compressor stator blade;
Fig. 5 is the right elevation of adsorption type gas compressor stator blade;
Fig. 6 is the sectional view of adsorption type gas compressor stator blade.Among the figure:
1. integral shroud 2. mounting holes 3. vacuum chambers 4. static pressure chambeies 5. blades, 6. baroports, 7. suction boles, 8. fixing pins
Embodiment
Embodiment one
Present embodiment is a kind of adsorption type gas compressor stator blade, is used for boundary layer suction and test are carried out in territory, gas compressor stator blade suction surface 0-50% leaf exhibition section.
As shown in Figure 1, present embodiment comprises blade 5 and integral shroud 1.At the blade tip place fixing pin 8 is arranged.The suction surface of blade 5 is distributed with 35 suction boles 7 and 7 baroports 6.
Said suction bole 7 is divided into 7 rows, and is evenly distributed between leading edge to the trailing edge of blade 5, and the distance of centre distance blade inlet edge of first row's suction bole 7 is 12% chord length, and the distance of the centre distance trailing edge of the 7th row's suction bole 7 is 28% chord length; The first row suction bole 7 is that 5% leaf is high apart from the distance of blade tip, and the 5th row suction bole 7 is that 45% leaf is high apart from the distance of blade tip.The aperture of suction bole 7 is 1.2mm.
Said baroport 6 has 7, becomes a column distribution from the leading edge place of blade 5 to the trailing edge place.Baroport 6 is between blade 5 the 5th row suction bole 7 and blade root, and each baroport 6 centre distance the 5th row suction bole 7 centre distance is 5mm.The center of 7 baroports 6 respectively with 7 row's suction boles 7 be centered close to same chordwise location.The diameter of baroport 6 is 0.8mm.During work,, aspirate the gas compressor Effect on Performance to confirm the blade surface boundary layer through the variation of static pressure before and after suction that baroport 6 is measured blade surface.
Shown in Fig. 1, Fig. 5～6.There are 7 vacuum chambers 3 and 7 static pressure chambeies 4 in the inside of blade 5; Vacuum chamber 3 connects integral shroud 1 with static pressure chamber 4.
The inner vacuum chamber 3 of said stator blade is a circular hole, and diameter is 2mm, and the high direction of the leaf from the blade root end face along blade 5 is extended to the blade tip place.Each vacuum chamber 3 is corresponding with the position of each row's suction bole 7 in the tangential position of stator blade; The center of each vacuum chamber 3 all is positioned on the center line of blade root place blade profile.The center line of said vacuum chamber 3 is vertical each other with the center line of suction bole 7.The even integral shroud of one end of each vacuum chamber 31 connects, the other end respectively with row's suction bole 7 in the hole dolly in each hole direct-connected logical.
Blade interior have 7 along chord of blade to the circular hole static pressure chamber 4 of arranging, the high direction of the leaf from the blade root end face along blade 5 is extended to the blade tip place, and with directly connect with the hole dolly of row's baroport 6 respectively.Described 7 static pressure chambeies 4 are corresponding with the position of each row's baroport 6 respectively in the tangential position of blade; And at blade 5 thickness directions, each static pressure chamber is between vacuum chamber 3 and blade suction surface; Distance between the center in the center of vacuum chamber 3 and static pressure chamber 4 is 4mm.The center line in said static pressure chamber 4 is vertical each other with the center line of baroport 6.The diameter in static pressure chamber 4 is 1mm.
During work, carry out the suction of blade surface boundary layer through suction bole 7 respectively, make the low energy gas of blade surface get into vacuum chamber 3, discharge through vacuum chamber 3 again, realize the boundary layer suction of blade surface through suction bole 7.7 baroports 6 reach the static pressure of blade surface in the static pressure chamber 4, reach the outside through static pressure chamber 4 again, and 7 baroports 6 carry out static pressure measurement simultaneously.
Embodiment two
Present embodiment is a kind of adsorption type gas compressor stator blade, is used for boundary layer suction and test are carried out in territory, gas compressor stator blade suction surface 45-100% leaf exhibition section.
As shown in Figure 1, present embodiment comprises blade 5 and integral shroud 1.At the blade tip place fixing pin 8 is arranged.The suction surface of blade 5 is distributed with 25 suction boles 7 and 5 baroports 6.
Said suction bole 7 is divided into 5 rows, and is evenly distributed between leading edge to the trailing edge of blade 5, and the distance of centre distance blade inlet edge of first row's suction bole 7 is 50% chord length, and the distance of the centre distance trailing edge of the 5th row's suction bole 7 is 10% chord length; The first row suction bole 7 is that 50% leaf is high apart from the distance of blade tip, and the 5th row suction bole 7 is that 95% leaf is high apart from the distance of blade tip.The aperture of suction bole 7 is 1.5mm.
Said baroport 6 has 5, becomes a column distribution from the leading edge place of blade 5 to the trailing edge place.Baroport 6 is between blade 5 first row suction boles 7 and blade tip, and the baroport 6 centre distance first row suction bole 7 centre distances are 3mm.The center of 5 baroports 6 respectively with 5 row's suction boles 7 be centered close to same chordwise location.The diameter of baroport 6 is 1mm.During work,, aspirate the gas compressor Effect on Performance to confirm the blade surface boundary layer through the variation of static pressure before and after suction that baroport 6 is measured blade surface.
Shown in Fig. 1, Fig. 5～6.There are 5 vacuum chambers 3 and 5 static pressure chambeies 4 in the inside of blade 5; Vacuum chamber 3 connects integral shroud 1 with static pressure chamber 4.
Said stator blade internal vacuum 3 is a circular hole, and diameter is 2mm, and the high direction of the leaf from the blade root end face along blade 5 is extended to the blade tip place.Each vacuum chamber 3 is corresponding with the position of each row's suction bole 7 in the tangential position of stator blade; The center of each vacuum chamber 3 all is positioned on the center line of blade root place blade profile.The center line of said vacuum chamber 3 is vertical each other with the center line of suction bole 7.One end of each vacuum chamber 3 connects integral shroud 1, the other end respectively with row's suction bole 7 in the hole dolly in each hole direct-connected logical.
Blade interior have 5 along chord of blade to the circular hole static pressure chamber 4 of arranging, the high direction of the leaf from the blade root end face along blade 5 is extended to the blade tip place, and with directly connect with the hole dolly of row's baroport 6 respectively.Described 5 static pressure chambeies 4 are corresponding with the position of each row's baroport 6 respectively in the tangential position of blade; And at blade 5 thickness directions, each static pressure chamber is between vacuum chamber 3 and blade pressure surface; Distance between the center in the center of vacuum chamber 3 and static pressure chamber 4 is 3mm.The center line in said static pressure chamber 4 is vertical each other with the center line of baroport 6.The diameter in static pressure chamber 4 is 1mm.
During work, carry out the suction of blade surface boundary layer through suction bole 7 respectively, make the low energy gas of blade surface get into vacuum chamber 3, discharge through vacuum chamber 3 again, realize the boundary layer suction of blade surface through suction bole 7.5 baroports 6 reach the static pressure of blade surface in the static pressure chamber 4, reach the outside through static pressure chamber 4 again, and 5 baroports 6 carry out static pressure measurement simultaneously.
Embodiment three
Present embodiment is a kind of adsorption type gas compressor stator blade, is used for boundary layer suction and test are carried out in territory, gas compressor stator blade suction surface 20-80% leaf exhibition section.
As shown in Figure 1, present embodiment comprises blade 5 and integral shroud 1.At the blade tip place fixing pin 8 is arranged.The suction surface of blade 5 is distributed with 90 suction boles 7 and 9 baroports 6.
Said suction bole 7 is divided into 9 rows, and 10 of every rows are evenly distributed between leading edge to the trailing edge of blade 5, and the distance of centre distance blade inlet edge of first row's suction bole 7 is 10% chord length, and the distance of the centre distance trailing edge of the 9th row's suction bole 7 is 15% chord length; The first row suction bole 7 is that 25% leaf is high apart from the distance of blade tip, and the 10th row suction bole 7 is that 75% leaf is high apart from the distance of blade tip.The aperture of suction bole 7 is 2mm.
Said baroport 6 has 9, becomes a column distribution from the leading edge place of blade 5 to the trailing edge place.Baroport 6 is between blade 5 the 10th row suction bole 7 and blade root, and last row suction bole 7 centre distances of baroport 6 centre distance are 2mm.The center of 9 baroports 6 respectively with 9 row's suction boles 7 be centered close to same chordwise location.The diameter of baroport 6 is 1.5mm.During work,, aspirate the gas compressor Effect on Performance to confirm the blade surface boundary layer through the variation of static pressure before and after suction that baroport 6 is measured blade surface.
Shown in Fig. 1, Fig. 5～6.There are 9 vacuum chambers 3 and 9 static pressure chambeies 4 in the inside of blade 5; Vacuum chamber 3 connects integral shroud 1 with static pressure chamber 4.
Said stator blade internal vacuum 3 is a circular hole, and diameter is 2mm, and the high direction of the leaf from the blade root end face along blade 5 is extended to the blade tip place.Each vacuum chamber 3 is corresponding with the position of each row's suction bole 7 in the tangential position of stator blade; The center of each vacuum chamber 3 all is positioned on the center line of blade root place blade profile.The center line of said vacuum chamber 3 is vertical each other with the center line of suction bole 7.One end of each vacuum chamber 3 connects integral shroud 1, the other end respectively with row's suction bole 7 in the hole dolly in each hole direct-connected logical.
Blade interior have 9 along chord of blade to the circular hole static pressure chamber 4 of arranging, the high direction of the leaf from the blade root end face along blade 5 is extended to the blade tip place, and with directly connect with the hole dolly of row's baroport 6 respectively.Described 9 static pressure chambeies 4 are corresponding with the position of each row's baroport 6 respectively in the tangential position of blade; And at blade 5 thickness directions, each static pressure chamber is between vacuum chamber 3 and blade suction surface; Distance between the center in the center of vacuum chamber 3 and static pressure chamber 4 is 3.5mm.The center line in said static pressure chamber 4 is vertical each other with the center line of baroport 6.The diameter in static pressure chamber 4 is 1mm.
Fixing pin 8 is positioned at the blade tip end of blade 5.The center of fixing pin 8 overlaps with the center line in blade tip cross section, and is positioned at the 70% chord length place in blade tip cross section.Fixing pin 8 end faces middle part has the groove that is connected with the gas compressor wheel hub.Described groove is along the tangential horizontal distribution of blade.
During work, carry out the suction of blade surface boundary layer through suction bole 7 respectively, make the low energy gas of blade surface get into vacuum chamber 3, discharge through vacuum chamber 3 again, realize the boundary layer suction of blade surface through suction bole 7.9 baroports 6 reach the static pressure of blade surface in the static pressure chamber 4, reach the outside through static pressure chamber 4 again, and 9 baroports 6 carry out static pressure measurement simultaneously.
Claims (4)
1. an adsorption type gas compressor stator blade is characterized in that,
A. described gas compressor stator blade comprises blade and integral shroud; There is fixing pin at the place at blade tip; The suction surface of blade is placed with a plurality of suction boles and a plurality of baroport; Said suction bole is evenly distributed between leading edge to the trailing edge of blade, and the distance of centre distance blade inlet edge of first row's suction bole is 10～50% chord lengths, and distance of the centre distance trailing edge of last row's suction bole is 10～28% chord lengths; The first row suction bole is that 5～50% leaves are high apart from the distance of blade tip, and last row suction bole is that 45～95% leaves are high apart from the distance of blade tip; The aperture of suction bole is 1.2～2mm;
B. the quantity of said baroport is identical with row's number of suction bole; Each baroport becomes a column distribution from the leading edge place of blade to the trailing edge place, and between suction bole and blade root or blade tip; The same chordwise location that is centered close to of suction bole is arranged at the center of each baroport respectively with each; Distance between the center of baroport and the center of adjacent suction bole is 2～5mm;
C. there is vacuum chamber and the static pressure chamber that connects with integral shroud the inside of blade; Wherein, the quantity of vacuum chamber is identical with row's number of suction bole; Each vacuum chamber is corresponding with the position of each row's suction bole in the tangential position of stator blade; The center of each vacuum chamber all is positioned on the center line of blade root place blade profile; The center line of said vacuum chamber is vertical each other with the center line of suction bole; One end of each vacuum chamber connects integral shroud, the other end respectively with row's suction bole in the hole dolly in each hole direct-connected logical; The quantity in said static pressure chamber is identical with the number of baroport; The center line in static pressure chamber is vertical each other with the center line of baroport; Described each static pressure chamber is corresponding with the position of each row's baroport respectively in the tangential position of blade; Distance between the center in the center of vacuum chamber and static pressure chamber is 3～4mm; Each static pressure chamber is the high direction of the leaf along blade from the blade root end face, extends to the blade tip place, and direct-connected logical with respectively with the hole dolly of row's baroport;
D. there is the through hole that is communicated with inner each vacuum chamber of blade and each static pressure chamber on the surface of integral shroud;
E. fixing pin is positioned at the blade tip end of blade; The center of fixing pin overlaps with the center line in blade tip cross section, and is positioned at 30～70% chord length places in blade tip cross section.
2. a kind of according to claim 1 adsorption type gas compressor stator blade is characterized in that the diameter of baroport is 0.8～1.5mm; The vacuum chamber diameter is 2mm, and static pressure chamber diameter is 1mm.
3. a kind of according to claim 1 adsorption type gas compressor stator blade is characterized in that, fixing pin end face middle part has the groove that is connected with the gas compressor wheel hub; Described groove is along the tangential horizontal distribution of blade.
4. a kind of according to claim 1 adsorption type gas compressor stator blade is characterized in that when baroport was between blade root and suction bole, the static pressure chamber was between vacuum chamber and blade suction surface; When baroport was between blade tip and suction bole, the static pressure chamber was between vacuum chamber and blade pressure surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201120327190XU CN202220756U (en) | 2011-09-01 | 2011-09-01 | Adsorption type compressor stator blade |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201120327190XU CN202220756U (en) | 2011-09-01 | 2011-09-01 | Adsorption type compressor stator blade |
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| CN202220756U true CN202220756U (en) | 2012-05-16 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201120327190XU Expired - Lifetime CN202220756U (en) | 2011-09-01 | 2011-09-01 | Adsorption type compressor stator blade |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102312860A (en) * | 2011-09-01 | 2012-01-11 | 西北工业大学 | Suction surface sucking stator blade of air compressor |
| CN103967812A (en) * | 2014-04-29 | 2014-08-06 | 西北工业大学 | Reverse-flow type counter-rotating adsorption gas compressor |
| CN107061329A (en) * | 2017-04-24 | 2017-08-18 | 浙江理工大学 | A kind of axial flow blower |
| CN110374688A (en) * | 2019-07-16 | 2019-10-25 | 中国航发沈阳发动机研究所 | A kind of multi-cavity stator structure and air-flow adsorption system |
| CN111140284A (en) * | 2020-01-16 | 2020-05-12 | 北京航空航天大学 | Handle type turbine blade with element-level front edge provided with five pressure sensing holes |
| CN112324713A (en) * | 2020-11-26 | 2021-02-05 | 沈阳航空航天大学 | Airflow corner self-adaptive guide blade of axial-flow compressor and design method thereof |
-
2011
- 2011-09-01 CN CN201120327190XU patent/CN202220756U/en not_active Expired - Lifetime
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102312860A (en) * | 2011-09-01 | 2012-01-11 | 西北工业大学 | Suction surface sucking stator blade of air compressor |
| CN102312860B (en) * | 2011-09-01 | 2013-04-24 | 西北工业大学 | Suction surface sucking stator blade of air compressor |
| CN103967812A (en) * | 2014-04-29 | 2014-08-06 | 西北工业大学 | Reverse-flow type counter-rotating adsorption gas compressor |
| CN107061329A (en) * | 2017-04-24 | 2017-08-18 | 浙江理工大学 | A kind of axial flow blower |
| CN110374688A (en) * | 2019-07-16 | 2019-10-25 | 中国航发沈阳发动机研究所 | A kind of multi-cavity stator structure and air-flow adsorption system |
| CN111140284A (en) * | 2020-01-16 | 2020-05-12 | 北京航空航天大学 | Handle type turbine blade with element-level front edge provided with five pressure sensing holes |
| CN112324713A (en) * | 2020-11-26 | 2021-02-05 | 沈阳航空航天大学 | Airflow corner self-adaptive guide blade of axial-flow compressor and design method thereof |
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Granted publication date: 20120516 Effective date of abandoning: 20130424 |
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