CN104454651A - Air inlet casing of centrifugal air compressor of micro-turbojet engine - Google Patents
Air inlet casing of centrifugal air compressor of micro-turbojet engine Download PDFInfo
- Publication number
- CN104454651A CN104454651A CN201410768745.2A CN201410768745A CN104454651A CN 104454651 A CN104454651 A CN 104454651A CN 201410768745 A CN201410768745 A CN 201410768745A CN 104454651 A CN104454651 A CN 104454651A
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- CN
- China
- Prior art keywords
- dovetail groove
- inlet casing
- micro
- air inlet
- jet engine
- 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.)
- Pending
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Classifications
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- 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
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
- F04D29/4213—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps suction ports
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- 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
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention belongs to the technical field of pneumatic stability of micro-turbojet engines, in particular to an air inlet casing of a centrifugal air compressor of a micro-turbojet engine. The air inlet casing comprises a casing body, an air inlet and an air inlet edge. A plurality of trapezoidal grooves which are peripherally and uniformly arranged are formed in the peripheral surface of the inner wall of the air inlet. The air inlet casing has the advantages of simple structure, excellent anti-surge effects of the air compressor, convenience in machining and assembling, low manufacturing cost and the like.
Description
Technical field
The invention belongs to miniature turbine jet engines aerodynamic stability technical field, specifically a kind of inlet casing of Micro Turbine Jet Engine centrifugal compressor.
Background technique:
Micro Turbine Jet Engine is the emerging field of turbo-power technical development.In recent years, fast development is able to due to military affairs and civilian demand energetically.In military affairs, Micro Turbine Jet Engine can be used as the power of micro-unmanned reconnaissance plane, micro-unmanned attack plane, the aircraft such as fly bomb and target drone that cruises, and this micro air vehicle will play an important role in unmanned electronics air battle in future, military surveillance, the over the ground Military Application such as Precise strike, fight-terrorism warfare; And civilian on, Micro Turbine Jet Engine can be used as the power of the miniplanes such as high speed model plane, micro-unmanned vidicon camera, the unmanned monitoring and warning machine in low latitude, and it has superior application prospect in national economy fields such as geodetic survey, meteorological observation, environmental monitoring, forest-fire prevention, overhead irrigation.Visible above, its operating conditions that extensively will cause of Micro Turbine Jet Engine application has complexity and polytrope, and this requires that Micro Turbine Jet Engine should have wider stable operation range.The surge remaining of centrifugal compressor is the principal element determining Micro Turbine Jet Engine working stability.Usual hope, when maintenance pressure ratio, efficiency are certain value, improve the surge remaining of gas compressor, increases its stable operation range.In order to make gas compressor have desirable surge remaining, selecting when pneumatic design and being conducive to gas compressor and expanding steady pneumatic and structural parameter.Meanwhile, also to take some anti-asthma measures, as intergrade venting, adjustable straightener(stator) blade, many rotor structures etc.Treated casing technology is current widely used anti-asthma measure, obtains domestic and international expert and unanimously approves.It is simple that it has structure, and anti-asthma is effective, be convenient to processing, assembling, the advantages such as low cost of manufacture, and these advantages just meeting the demand of Micro Turbine Jet Engine.Treated casing technology anti-asthma principle: the front end and back end due to groove during blade rotary exists pressure reduction, the front portion of such groove can produce jet flow, and the discrete leakage vortex in the blade tip back side is oppressed or blown down to this burst of jet flow, prevents airflow breakaway, avoid or postponed the surge of gas compressor.Test shows compressor surge often by blade tip, then brings out the panting of complete machine air-flow, handles tip air-flow (comprising leakage vortex) as seen well extremely important.Treated casing technology is the effective stability enhancement method of one generally used both at home and abroad, and it is very great that this technology is applied to Micro Turbine Jet Engine field meaning.At present, the Theoretical Design of treated casing form is ripe not enough, and the enforcement of new departure is mainly completed by research technique.The successful processor box form of a kind of novelty should in the surge remaining not reducing or improve by a relatively large margin under seldom reducing compressor efficiency prerequisite gas compressor.The measure of gas compressor anti-asthma divides initiatively and passive two kinds usually, and if intergrade venting, adjustable straightener(stator) blade, blade back air-breathing etc. are active measures, many rotor structures, treated casing etc. belong to passive measure.Many complex rotor structures seldom adopt in Micro Turbine Jet Engine, and it is simple that processor box has structure, and anti-asthma is effective, and be convenient to processing, assembling, the advantages such as low cost of manufacture, Micro Turbine Jet Engine is required just for this.
Summary of the invention
The present invention is to solve how to reduce the problem of compressor surge remaining, provide a kind of inlet casing of Micro Turbine Jet Engine centrifugal compressor.
Present invention employs following technological scheme:
The inlet casing of Micro Turbine Jet Engine centrifugal compressor, it comprises casing body and suction port, suction port edge, and described suction port inwall side face is provided with the dovetail groove that some circumferences are evenly arranged.
Described dovetail groove is set to inclination, and quantity is provided with 50-70 bar.
The described long 27mm of dovetail groove waist, top margin is long is 1.5mm, and bottom side length is 2.5mm, and the groove depth of dovetail groove is 5.5mm.
The both sides sidewall of described dovetail groove becomes the angle of 25 ° with radial direction, the true dip direction of this dovetail groove is contrary with vane rotary direction.
The top of described dovetail groove and the distance at suction port edge are 18.5mm.
Advantage of the present invention is that structure is simple, and anti-asthma is effective, is convenient to processing, assembling, low cost of manufacture etc.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention;
Fig. 2 is a portion enlarged view of Fig. 1;
Fig. 3 is that the H-H of Fig. 1 is to sectional view;
Fig. 4 is the b portion enlarged view of Fig. 3.
Embodiment
As shown in Figure 1, the inlet casing of Micro Turbine Jet Engine centrifugal compressor, it comprises casing body 1 and suction port 2, suction port edge 3, the precision casting of centrifugal compressor inlet casing body aluminium material forms, and described suction port 2 inwall side face is provided with the dovetail groove 4 that some circumferences are evenly arranged.
As shown in Figure 3, dovetail groove be set to tilt, the true dip direction of this dovetail groove is contrary with vane rotary direction R, and quantity is provided with 50-70 bar, and what adopt in this specific embodiment is 60; Processor box is without circumferential inner-cavity structure, to keep compressor efficiency, dovetail groove circumference is uniformly distributed, have 60, there is pressure reduction in the front end and back end due to groove when its working procedure is blade rotary, the front portion of such groove can produce jet flow, and the discrete leakage vortex in the blade tip back side is oppressed or blown down to this burst of jet flow, prevent airflow breakaway, avoid or postponed the surge of gas compressor.
As shown in Figure 2, the long 27mm of dovetail groove waist, top margin is long is 1.5mm, and bottom side length is 2.5mm, and the groove depth of dovetail groove is 5.5mm, and this trapezoid groove structure can increase the injection intensity of air-flow, strengthens the blowing to leakage vortex and suppression.
As shown in Figure 4, the both sides sidewall of dovetail groove with radial become the angle of 25 °, the true dip direction of this dovetail groove is contrary with vane rotary direction, and it acts on is be conducive to compressing to leakage vortex and blowing, makes it be difficult to separation at blade back.
As shown in Figure 2, the top of dovetail groove and the distance at suction port edge are 18.5mm, and this size is optimized by test.
Claims (5)
1. the inlet casing of Micro Turbine Jet Engine centrifugal compressor, it comprises casing body and suction port, suction port edge, it is characterized in that: described suction port inwall side face is provided with the dovetail groove that some circumferences are evenly arranged.
2. the inlet casing of Micro Turbine Jet Engine centrifugal compressor according to claim 1, is characterized in that: described dovetail groove be set to tilt, quantity is provided with 50-70 bar.
3. the inlet casing of Micro Turbine Jet Engine centrifugal compressor according to claim 1 and 2, is characterized in that: the described long 27mm of dovetail groove waist, and top margin is long is 1.5mm, and bottom side length is 2.5mm, and the groove depth of dovetail groove is 5.5mm.
4. the inlet casing of Micro Turbine Jet Engine centrifugal compressor according to claim 1 and 2, is characterized in that: the both sides sidewall of described dovetail groove becomes the angle of 25 ° with radial direction, the true dip direction of this dovetail groove is contrary with vane rotary direction.
5. the inlet casing of Micro Turbine Jet Engine centrifugal compressor according to claim 1 and 2, is characterized in that: the top of described dovetail groove and the distance at suction port edge are 18.5mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410768745.2A CN104454651A (en) | 2014-12-12 | 2014-12-12 | Air inlet casing of centrifugal air compressor of micro-turbojet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410768745.2A CN104454651A (en) | 2014-12-12 | 2014-12-12 | Air inlet casing of centrifugal air compressor of micro-turbojet engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104454651A true CN104454651A (en) | 2015-03-25 |
Family
ID=52901232
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410768745.2A Pending CN104454651A (en) | 2014-12-12 | 2014-12-12 | Air inlet casing of centrifugal air compressor of micro-turbojet engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104454651A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109667669A (en) * | 2018-12-28 | 2019-04-23 | 中国科学院工程热物理研究所 | Gas turbine inlet air casing |
| WO2023017718A1 (en) * | 2021-08-12 | 2023-02-16 | 株式会社Ihi | Centrifugal compressor and supercharger |
-
2014
- 2014-12-12 CN CN201410768745.2A patent/CN104454651A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109667669A (en) * | 2018-12-28 | 2019-04-23 | 中国科学院工程热物理研究所 | Gas turbine inlet air casing |
| WO2023017718A1 (en) * | 2021-08-12 | 2023-02-16 | 株式会社Ihi | Centrifugal compressor and supercharger |
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|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20150325 |