CN109751253A - A kind of big-flow high-pressure suitable for small size gas turbine is than one-stage centrifugal compressor - Google Patents
A kind of big-flow high-pressure suitable for small size gas turbine is than one-stage centrifugal compressor Download PDFInfo
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- CN109751253A CN109751253A CN201711062414.7A CN201711062414A CN109751253A CN 109751253 A CN109751253 A CN 109751253A CN 201711062414 A CN201711062414 A CN 201711062414A CN 109751253 A CN109751253 A CN 109751253A
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Abstract
The invention discloses a kind of big-flow high-pressures suitable for small size gas turbine than one-stage centrifugal compressor, belong to the technical field of turbomachine compressor, its key is one-stage centrifugal to calm the anger in the case where big flow to realize high pressure ratio, while compressor efficiency with higher.Centrifugal compressor rotary part centrifugal impeller specific speed control of the present invention is within the scope of efficiency optimization, air-flow has very high kinetic energy after centrifugal impeller outflow, the kinetic energy of the air-flow overwhelming majority is converted pressure energy by the radial vaned diffuser specially designed, and guarantees do not occur serious separation area in radial diffuser blade path.Based on big-flow high-pressure of the invention than one-stage centrifugal compressor technology, multistage compressor scheme used by existing 3-10MW small size gas turbine can be greatly simplified, the performance requirement of gas turbine can be met only with one-stage centrifugal compressor, this will substantially reduce the cost of small size gas turbine, greatly promote the gas turbine competitiveness of product in market.
Description
Technical field
The invention belongs to impeller rotating machinery fields, and in particular to a kind of big-flow high-pressure suitable for small size gas turbine
Than single-stage high-speed centrifugal compressor and using the 3-10MW small size gas turbine of the compressor.
Background technique
The conventional centrifugal compressor application traffic range overwhelming majority be lower than axial flow compressor and mixed-flow compressor, but with from
The continuous promotion of heart compressor pneumatic design technology, centrifugal compressor can break through the previous range of flow upper limit, be applied to more
In big range of flow.Therefore, on specific products application, the technical solution of multi stage axial flow compressor will be greatly simplified, can
Use the less centrifugal compressor of series or even one-stage centrifugal compressor, it will be able to meet performance requirement.
Currently there are 3-10MW power grade small size gas turbine compressor part mostly use multistage axial flow pressure
Mechanism of qi scheme, series be up to ten what.Such as: the C40 type gas turbine of Sola Corp., the U.S..If can pneumatically setting in compressor
It realizes and breaks through on meter, the purpose of the gas boosting of gas turbine is only completed with single-stage compressor, existing 3- will be greatly simplified
10MW small size gas turbine structure reduces the production cost and assembly difficulty of manufacture.
A kind of big-flow high-pressure suitable for small size gas turbine proposed by the present invention is adopted than single-stage high-speed centrifugal compressor
With the centrifugal compressor design and parser optimization design of independent development, the efficient centrifugal impeller of configuration high-speed, blade tail
The radial vaned diffuser of edge specially treated and conventional axial diffuser.
Summary of the invention
The purpose of the embodiment of the present invention is that providing a kind of big-flow high-pressure for being suitable for small size gas turbine compares single-stage high-speed
Centrifugal compressor, mainly for the small size gas turbine of 3-10MW power grade.
A kind of big-flow high-pressure being suitable for small size gas turbine proposed by the present invention than single-stage high-speed centrifugal compressor,
Structure includes: centrifugal impeller, radial vaned diffuser and axial diffuser.
The centrifugal impeller has the feature that overall pressure tatio is greater than 8.5, and import wheel hub ratio is not less than 0.4, and revolving speed is greater than
18000 revs/min, import hub diameter and impeller outlet outer diameter ratio are less than 0.26, and impeller linear velocity is up to 620m/s or more.
Optionally, centrifugal impeller can be for band splitterr vanes or without splitterr vanes pattern.
The radial direction vaned diffuser is the optimization version of wedge-shaped diffuser, and diffuser blade pressure face trailing edge part is designed to
Transition circle camber or ellipse can be avoided air-flow in this region compared with conventional wedge-shaped diffuser blade trailing edge linear type
There is a wide range of separation, to achieve the purpose that reduce flow losses, raising efficiency.
The axial diffuser is using airfoil diffuser conventional at present.
Optionally, axial diffuser can be no blade profile, blade type, channel-style etc..
Optionally, a row or two rows of concatenated structure layout patterns can be used in axis stream diffuser.
The invention further relates to a kind of small size gas turbines of 3-10MW power grade, using above-described big-flow high-pressure
Than single-stage high-speed centrifugal compressor.
The 3-10MW small size gas turbine of one-stage centrifugal compressor based on technical solution of the present invention has compressor stage
The features such as number is less, structure is simple, manufacturing cost is low, product competitiveness in the market is strong.
Detailed description of the invention
In order to illustrate the technical solution of the embodiments of the present invention more clearly, required use in being described below to embodiment
Attached drawing be briefly described, it should be apparent that, drawings in the following description are only some embodiments of the invention, for this
For the those of ordinary skill of field, without creative efforts, it can also be obtained according to these attached drawings others
Attached drawing.
Fig. 1 is three-dimensional model diagram of the big-flow high-pressure of the invention implemented than single-stage high-speed centrifugal compressor.
Description of symbols:
1, centrifugal impeller；2, radial vaned diffuser；3, axial diffuser.
Fig. 2 is that the designed a big-flow high-pressure that numerical simulation calculation obtains is more total than single-stage high-speed centrifugal compressor
Pressure ratio distribution curve.
Fig. 3 is that the designed a big-flow high-pressure that numerical simulation calculation obtains is more exhausted than single-stage high-speed centrifugal compressor
Thermal efficiency distribution curve.
Specific embodiment
In order to make the objectives, technical solutions and advantages of the present invention clearer, With reference to embodiment and join
According to attached drawing, the present invention is described in more detail.It should be understood that these descriptions are merely illustrative, and it is not intended to limit this hair
Bright range.In addition, in the following description, descriptions of well-known structures and technologies are omitted, to avoid this is unnecessarily obscured
The concept of invention.
As shown in Figure 1, the invention proposes a kind of big-flow high-pressure for being suitable for small size gas turbine than single-stage high-speed from
Heart compressor specifically includes that centrifugal impeller 1, radial vaned diffuser 2 and axial diffuser 3.Air enters from atmospheric environment
Centrifugal compressor is pressurized by high-speed rotary part centrifugal impeller 1, will be from centrifugal impeller 1 by radial vaned diffuser 2
The kinetic energy of the compressed gas of outflow is converted into pressure energy to the full extent, and guides air-flow in radial 2 runner of vaned diffuser
Uniform Flow, final air-flow turn to axial diffuser 3 by 90 degree of bend pipes, realize that air-flow is calmed the anger from axial direction outflow centrifugation
Machine, into the combustion chamber of gas turbine.
Specific embodiment is 15kg/s with a flow, is carried out based on the single-stage high-speed centrifugal compressor that overall pressure tatio is 9
It is discussed in detail, the requirement of the performance indicator of this centrifugal compressor and the small size gas turbine of 3MW or so to compressibility is close.
After optimization design, 1 overall pressure tatio 9.7 of centrifugal impeller, import wheel hub go out than 0.4, import hub diameter and impeller
Mouth outer diameter ratio 0.22, impeller outlet linear velocity 645m/s, impeller blade export the high 18mm of leaf, are milled using five axis of titanium alloy material
System.
The radial vaned diffuser number of blade 19, blade pressure surface trailing edge part are designed to ellipse, and guidance air-flow uniformly leads to
Cross diffuser vane channel.
To verify designed Capability of Compressor, its overall pressure tatio and insulation are obtained by the way of Computer Numerical Simulation
Efficiency distribution curve, as shown in Figures 2 and 3.Calculated result is shown: in design discharge 15kg/s, the stagnation pressure of centrifugal compressor
Than being higher than 9, adiabatic efficiency has reached 81%, while obtaining high pressure ratio, compressor adiabatic efficiency with higher.From figure
We can also be seen that designed compressor has wider surge margin.
It should be understood that above-mentioned specific embodiment of the invention is used only for exemplary illustration or explains of the invention
Principle, but not to limit the present invention.Therefore, that is done without departing from the spirit and scope of the present invention is any
Modification, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.In addition, appended claims purport of the present invention
Covering the whole variations fallen into attached claim scope and boundary or this range and the equivalent form on boundary and is repairing
Change.
Claims (4)
1. a kind of big-flow high-pressure suitable for small size gas turbine includes: than one-stage centrifugal compressor, the centrifugal compressor
Centrifugal impeller, radial vaned diffuser and axial diffuser；Air-flow is pressurized by rotary part centrifugal impeller, has leaf using radial
Most kinetic energy are converted pressure energy by diffuser, promotes the static pressure of air-flow, then gradually goes to axis stream by axial diffuser
Flow out compressor in direction.
2. centrifugal impeller according to claim 1, it is characterised in that: overall pressure tatio is greater than 8.5, and import wheel hub ratio is not less than
0.4, revolving speed is greater than 18000 revs/min, and import hub diameter and impeller outlet outer diameter ratio are less than 0.26, impeller outlet linear speed
It spends up to 620m/s or more.
3. radial direction vaned diffuser according to claim 1, it is characterised in that: diffuser blade pressure face trailing edge region is set
Transition circle camber or ellipse are counted into, compared with conventional wedge-shaped diffuser blade trailing edge linear type, can be avoided air-flow herein
There is a wide range of separation in region, helps to reduce flow losses, promotes compressor efficiency.
4. a kind of small size gas turbine according to claim 1, comprising: use big flow according to claim 1
High pressure ratio single-stage high-speed centrifugal compressor, combustion turbine power grade is between 3-10MW.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711062414.7A CN109751253A (en) | 2017-11-02 | 2017-11-02 | A kind of big-flow high-pressure suitable for small size gas turbine is than one-stage centrifugal compressor |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711062414.7A CN109751253A (en) | 2017-11-02 | 2017-11-02 | A kind of big-flow high-pressure suitable for small size gas turbine is than one-stage centrifugal compressor |
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| CN109751253A true CN109751253A (en) | 2019-05-14 |
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Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CH229267A (en) * | 1942-05-04 | 1943-10-15 | Michael Dipl Ing Martinka | Centrifugal compressor. |
| US6488469B1 (en) * | 2000-10-06 | 2002-12-03 | Pratt & Whitney Canada Corp. | Mixed flow and centrifugal compressor for gas turbine engine |
| JP2005226558A (en) * | 2004-02-13 | 2005-08-25 | Honda Motor Co Ltd | Centrifugal compressor for gas turbine engine |
| CN101263306A (en) * | 2005-09-13 | 2008-09-10 | 英格索尔-兰德公司 | Diffuser for a centrifugal compressor |
| CN104895841A (en) * | 2015-04-30 | 2015-09-09 | 中国科学院工程热物理研究所 | Rectifier, runner structure, combined gas compressor and aviation gas turbine engine |
| CN204828040U (en) * | 2015-08-20 | 2015-12-02 | 深圳智慧能源技术有限公司 | Centrifugal compressor and impeller thereof |
| CN205401248U (en) * | 2016-03-23 | 2016-07-27 | 上海钛灵特压缩机有限公司 | Tooth -like transmission centrifugal compressor diffuser |
| CN106939832A (en) * | 2017-04-27 | 2017-07-11 | 中国科学院工程热物理研究所 | A kind of axle wander about as a refugee the heart blisk formula combination compressibility |
| CN116838623A (en) * | 2023-06-21 | 2023-10-03 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Ultra-compact wide-speed-domain combined compressor structure |
-
2017
- 2017-11-02 CN CN201711062414.7A patent/CN109751253A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CH229267A (en) * | 1942-05-04 | 1943-10-15 | Michael Dipl Ing Martinka | Centrifugal compressor. |
| US6488469B1 (en) * | 2000-10-06 | 2002-12-03 | Pratt & Whitney Canada Corp. | Mixed flow and centrifugal compressor for gas turbine engine |
| JP2005226558A (en) * | 2004-02-13 | 2005-08-25 | Honda Motor Co Ltd | Centrifugal compressor for gas turbine engine |
| CN101263306A (en) * | 2005-09-13 | 2008-09-10 | 英格索尔-兰德公司 | Diffuser for a centrifugal compressor |
| CN104895841A (en) * | 2015-04-30 | 2015-09-09 | 中国科学院工程热物理研究所 | Rectifier, runner structure, combined gas compressor and aviation gas turbine engine |
| CN204828040U (en) * | 2015-08-20 | 2015-12-02 | 深圳智慧能源技术有限公司 | Centrifugal compressor and impeller thereof |
| CN205401248U (en) * | 2016-03-23 | 2016-07-27 | 上海钛灵特压缩机有限公司 | Tooth -like transmission centrifugal compressor diffuser |
| CN106939832A (en) * | 2017-04-27 | 2017-07-11 | 中国科学院工程热物理研究所 | A kind of axle wander about as a refugee the heart blisk formula combination compressibility |
| CN116838623A (en) * | 2023-06-21 | 2023-10-03 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Ultra-compact wide-speed-domain combined compressor structure |
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