CN109458359A - A kind of blade profile improving helium compressor single-stage pressure ratio - Google Patents
A kind of blade profile improving helium compressor single-stage pressure ratio Download PDFInfo
- Publication number
- CN109458359A CN109458359A CN201811600007.1A CN201811600007A CN109458359A CN 109458359 A CN109458359 A CN 109458359A CN 201811600007 A CN201811600007 A CN 201811600007A CN 109458359 A CN109458359 A CN 109458359A
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- CN
- China
- Prior art keywords
- blade profile
- helium compressor
- arc surface
- pressure ratio
- curvature
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- 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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Links
- 229910052734 helium Inorganic materials 0.000 title claims abstract description 21
- 239000001307 helium Substances 0.000 title claims abstract description 21
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 title claims abstract description 21
- 230000007704 transition Effects 0.000 claims abstract description 4
- 239000000203 mixture Substances 0.000 claims description 5
- 230000008676 import Effects 0.000 claims description 4
- 238000000034 method Methods 0.000 abstract description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 230000000704 physical effect Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 230000007306 turnover Effects 0.000 description 1
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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
- F04D29/384—Blades characterised by form
- F04D29/386—Skewed blades
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
A kind of blade profile improving helium compressor single-stage pressure ratio, it is related to a kind of Compressor airfoil, to solve the problems, such as that existing helium compressor single-stage pressure ratio is very low.Under the premise of efficiency meets, the method for increase series is generallyd use to improve the pressure ratio of helium compressor, but can do the axial dimension for increasing helium compressor in this way, increases whole size.Blade profile of the present invention is made of leading edge, trailing edge, suction surface and pressure face；Pressure face and suction surface are oppositely arranged, and the two sides of pressure face and suction surface pass through arc surface transition, pressure face outwardly convex, suction surface concaves, the curvature of one of arc surface is bigger than the curvature of another arc surface, and the biggish arc surface of curvature is leading edge, and the lesser arc surface of curvature is trailing edge；The geometry deflection angle of the blade profile is 30 °~50 °, and the inlet air flow angle of the blade profile is 20 °~60 °.The present invention is suitable for the movable vane piece and stator blade of helium compressor.
Description
Technical field
The present invention relates to a kind of Compressor airfoils, and in particular to a kind of blade profile for improving helium compressor single-stage pressure ratio.
Background technique
Because helium is more excellent than the physical property of air, and it is used for shrouded turbine engine as working medium.Existing helium
Compressor, single-stage pressure ratio is very low, in the case where meeting efficiency, generallys use the method for increase series to improve helium compressor
Efficiency, but in this way can do increase helium compressor axial dimension, increase whole size, occupy biggish space.
Summary of the invention
The present invention is very low in order to solve the problems, such as existing helium compressor single-stage pressure ratio, and provides a kind of raising helium pressure
The blade profile of mechanism of qi single-stage pressure ratio.
The technical solution adopted by the present invention to solve the above technical problem is:
The blade profile is made of leading edge, trailing edge, suction surface and pressure face；
Pressure face and suction surface are oppositely arranged, and by arc surface transition, pressure is faced out for the two sides of pressure face and suction surface
Protrusion, suction surface concave, and the curvature of one of arc surface is bigger than the curvature of another arc surface, the biggish arc surface of curvature
For leading edge, the lesser arc surface of curvature is trailing edge, and first increase of the thickness of the blade profile from leading edge to trailing edge reduces again；
The geometry deflection angle of the blade profile is 30 °~50 °, and the inlet air flow angle of the blade profile is 20 °~60 °.
Further, the outlet flow angle of the blade profile is -20 °~0 °.
Further, the air inlet angle of attack of the blade profile is -2 °~2 °.
Further, cascade solidity is between 0.8-1.5.
Further, the import geometry angle of the blade profile is 18 °~62 °.
Compared with the prior art, the invention has the following beneficial effects:
Geometry deflection angle of the invention is 30 °~50 °, increases the deflection angle of air-flow, the acting ability enhancing of leaf grating, together
When for avoid leaf grating suction surface trailing edge air-flow separate, need to reduce inlet air flow angle, thus by inlet air flow angle be set as 20 °~
60 °, leaf grating import geometry angle also reduces therewith, and the pressure for finally obtaining air stream outlet increases, and applies the present invention in helium
On compressor, single-stage pressure ratio can be significantly improved, and then meets the pressure ratio of helium compressor under the case where not increasing series.
Detailed description of the invention
Fig. 1 is schematic diagram of the invention.
Specific embodiment
Specific embodiment 1: illustrating present embodiment in conjunction with Fig. 1, blade profile described in present embodiment is by leading edge 1, trailing edge
2, suction surface 3 and pressure face 4 form；
Pressure face 4 and suction surface 3 are oppositely arranged, and the two sides of pressure face 4 and suction surface 3 pass through arc surface transition, pressure face 4
Outwardly convex, suction surface 3 concave, and the curvature of one of arc surface is bigger than the curvature of another arc surface, and curvature is biggish
Arc surface is leading edge 1, and the lesser arc surface of curvature is trailing edge 2, and first increase of the thickness of the blade profile from leading edge 1 to trailing edge 2 is again
Reduce；
The geometry deflection angle of the blade profile is 30 °~50 °, the inlet air flow angle beta of the blade profile1It is 20 °~60 °.
Specific embodiment 2: illustrate present embodiment in conjunction with Fig. 1, the outlet flow angle of blade profile described in present embodiment
β2It is -20 °~0 °.
So set, working as inlet air flow angle beta1One timing, exit flow angle beta2Bigger, air-flow turnover ability is bigger, pressure ratio
It is higher.
Other compositions and connection relationship are same as the specific embodiment one.
Specific embodiment 3: illustrate present embodiment in conjunction with Fig. 1, the air inlet angle of attack i of blade profile described in present embodiment
It is -2 °~2 °.
So set, preventing the trailing edge 2 of air-flow through the invention from generating separation, and then propose the efficiency of compressor
It rises.
Other compositions and connection relationship are same as the specific embodiment one.
Specific embodiment 4: present embodiment cascade solidity is between 0.8-1.5.
When cascade solidity of the present invention is 0.8-1.5, when air-flow flows through the present invention, the flow inlet angle of air-flow reaches critical value,
Air-flow deflection angle is not further added by this time, and leaf grating acting of the invention is in steady state.
Other compositions and connection relationship are same as the specific embodiment one.
Specific embodiment 5: illustrate present embodiment in conjunction with Fig. 1, the import geometry angle of blade profile described in present embodiment
β1AIt is 18 °~62 °.
Other compositions and connection relationship are same as the specific embodiment one.
Claims (5)
1. it is a kind of improve helium compressor single-stage pressure ratio blade profile, it is characterised in that: the blade profile by leading edge (1), trailing edge (2),
Suction surface (3) and pressure face (4) composition；
Pressure face (4) and suction surface (3) are oppositely arranged, and the two sides of pressure face (4) and suction surface (3) pass through arc surface transition, pressure
Power face (4) outwardly convex, suction surface (3) concave, and the curvature of one of arc surface is bigger than the curvature of another arc surface, bent
The biggish arc surface of rate is leading edge (1), and the lesser arc surface of curvature is trailing edge (2), and the thickness of the blade profile is from leading edge (1) to tail
Edge (2) first increases to be reduced again；
The geometry deflection angle of the blade profile is 30 °~50 °, the inlet air flow angle (β of the blade profile1) it is 20 °~60 °.
2. a kind of blade profile for improving helium compressor single-stage pressure ratio according to claim 1, it is characterised in that: the blade profile
Outlet flow angle (β2) it is -20 °~0 °.
3. a kind of blade profile for improving helium compressor single-stage pressure ratio according to claim 1, it is characterised in that: the blade profile
The air inlet angle of attack (i) be -2 °~2 °.
4. a kind of blade profile for improving helium compressor single-stage pressure ratio according to claim 1, it is characterised in that: cascade solidity
Between 0.8-1.5.
5. a kind of blade profile for improving helium compressor single-stage pressure ratio according to claim 1, it is characterised in that: the blade profile
Import geometry angle (β1A) it is 18 °~62 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811600007.1A CN109458359A (en) | 2018-12-26 | 2018-12-26 | A kind of blade profile improving helium compressor single-stage pressure ratio |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811600007.1A CN109458359A (en) | 2018-12-26 | 2018-12-26 | A kind of blade profile improving helium compressor single-stage pressure ratio |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109458359A true CN109458359A (en) | 2019-03-12 |
Family
ID=65614904
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811600007.1A Pending CN109458359A (en) | 2018-12-26 | 2018-12-26 | A kind of blade profile improving helium compressor single-stage pressure ratio |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111079236A (en) * | 2019-12-12 | 2020-04-28 | 中国船舶重工集团公司第七0三研究所 | Mother model machine matching point obtaining method for ship gas turbine compressor capacity increasing |
| CN113513500A (en) * | 2021-07-14 | 2021-10-19 | 南京航空航天大学 | Low-loss diffusion vane profile with negative outlet airflow angle |
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| CN102852857A (en) * | 2012-09-28 | 2013-01-02 | 哈尔滨工业大学 | High-load super transonic axial gas compressor aerodynamic design method |
| CN102927050A (en) * | 2012-10-24 | 2013-02-13 | 哈尔滨汽轮机厂有限责任公司 | End-bend blade for improving working stability of gas compressor |
| RU155495U1 (en) * | 2015-03-26 | 2015-10-10 | Открытое Акционерное Общество "Уфимское Моторостроительное Производственное Объединение" (Оао "Умпо") | GAS-TURBINE ENGINE LOW PRESSURE ROTOR WHEEL BLADE |
| CN106870465A (en) * | 2017-02-24 | 2017-06-20 | 中国科学院工程热物理研究所 | A kind of compressor, gas turbine and compressor stability-enhancement synergistic method |
| CN107061314A (en) * | 2017-03-28 | 2017-08-18 | 沈阳冠能燃气轮机科技有限公司 | The low-pressure compressor changed a social system using retired engine |
| CN209164176U (en) * | 2018-12-26 | 2019-07-26 | 中国船舶重工集团公司第七0三研究所 | A kind of blade profile improving helium compressor single-stage pressure ratio |
-
2018
- 2018-12-26 CN CN201811600007.1A patent/CN109458359A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH02248693A (en) * | 1989-03-23 | 1990-10-04 | Matsushita Seiko Co Ltd | Multiblade fan |
| CN2274699Y (en) * | 1996-03-21 | 1998-02-18 | 孙敏超 | Centripetal turbine wheel radial and combined flow |
| CN101666344A (en) * | 2008-09-03 | 2010-03-10 | 中国科学院工程热物理研究所 | Stability-enhancement synergistic method for controlling plasma flow |
| CN201310490Y (en) * | 2008-11-04 | 2009-09-16 | 秦彪 | Electronic radiating fan |
| CN101915130A (en) * | 2010-06-25 | 2010-12-15 | 北京理工大学 | Three-dimensional nozzle ring vane of variable geometry turbocharger and design method thereof |
| CN102852857A (en) * | 2012-09-28 | 2013-01-02 | 哈尔滨工业大学 | High-load super transonic axial gas compressor aerodynamic design method |
| CN102927050A (en) * | 2012-10-24 | 2013-02-13 | 哈尔滨汽轮机厂有限责任公司 | End-bend blade for improving working stability of gas compressor |
| RU155495U1 (en) * | 2015-03-26 | 2015-10-10 | Открытое Акционерное Общество "Уфимское Моторостроительное Производственное Объединение" (Оао "Умпо") | GAS-TURBINE ENGINE LOW PRESSURE ROTOR WHEEL BLADE |
| CN106870465A (en) * | 2017-02-24 | 2017-06-20 | 中国科学院工程热物理研究所 | A kind of compressor, gas turbine and compressor stability-enhancement synergistic method |
| CN107061314A (en) * | 2017-03-28 | 2017-08-18 | 沈阳冠能燃气轮机科技有限公司 | The low-pressure compressor changed a social system using retired engine |
| CN209164176U (en) * | 2018-12-26 | 2019-07-26 | 中国船舶重工集团公司第七0三研究所 | A kind of blade profile improving helium compressor single-stage pressure ratio |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111079236A (en) * | 2019-12-12 | 2020-04-28 | 中国船舶重工集团公司第七0三研究所 | Mother model machine matching point obtaining method for ship gas turbine compressor capacity increasing |
| CN113513500A (en) * | 2021-07-14 | 2021-10-19 | 南京航空航天大学 | Low-loss diffusion vane profile with negative outlet airflow angle |
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Application publication date: 20190312 |