CN104948473A - Spiral compressor for aviation gas turbine engine - Google Patents
Spiral compressor for aviation gas turbine engine Download PDFInfo
- Publication number
- CN104948473A CN104948473A CN201510338686.XA CN201510338686A CN104948473A CN 104948473 A CN104948473 A CN 104948473A CN 201510338686 A CN201510338686 A CN 201510338686A CN 104948473 A CN104948473 A CN 104948473A
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- Prior art keywords
- compressor
- spiral
- compressor blade
- turbine engine
- gas turbine
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Abstract
The invention discloses a spiral compressor for an aviation gas turbine engine. The compressor comprises a spiral shaft and a rotating shaft. The spiral shaft comprises a compressor blade and a hollow shaft, the compressor blade is of a spiral integral structure, edge strips are arranged on the edge of the compressor blade, the compressor blade is integrally arranged on an outer wall of the hollow shaft, and the rotating shaft is sleeved with the hollow shaft and rotates to drive the spiral shaft to rotate. The spiral compressor integrates the advantages of an axial flow type compressor and a centrifugal-flow compressor and is simple in structure and easy to manufacture.
Description
Technical field
The present invention relates to aero engine technology field, particularly relate to a kind of spiral aero gas turbine engine gas compressor.
Background technique
Gas compressor is one of critical piece of aero gas turbine engine, and its effect is exactly flow through air flow pressure to the acting of flow through air-flow to improve.At present, existing aero gas turbine engine gas compressor has two large classes, and one is centrifugal-flow compressor, and single stage supercharging ratio (increasing air flow pressure ratio before and after ratio and gas compressor) is large, but generally can not exceed two-stage; Another kind is axial-flow compressor, and single stage supercharging, than little, multistagely can be combined, but which increase engine weight.In order to obtain large pressure ratio and alleviate engine weight, at present, some motor is that axial flow and centrifugal-flow compressor are combined, and this adds engine component quantity and such engine structure relative complex to a certain extent, not easily manufactures.
Summary of the invention
Goal of the invention: in order to overcome the deficiencies in the prior art, the invention provides a kind of spiral aero gas turbine engine gas compressor, has merged the advantage of axial flow and centrifugal-flow compressor, and structure is simple, is easy to manufacture.
Technological scheme: for achieving the above object, the technical solution used in the present invention is:
A kind of spiral aero gas turbine engine gas compressor, comprise screw axis and running shaft, described screw axis comprises compressor blade and hollow shaft, described compressor blade is spirality overall structure, the edge of described compressor blade is provided with edge strip, described compressor blade integrated setting is at hollow shaft outer wall, and described rotary sleeve is located at hollow shaft inside, and running shaft rotates and drives screw axis to rotate.
Further, described compressor blade is left hand screw or right-hand screw, and the spiral number of turns is 1-50 circle.
Further, the angle between described edge strip and compressor blade edge is 0-180 °, and described edge strip continues along the Hand of spiral of compressor blade.
Further, described compressor blade and hollow shaft are overall structure.
Beneficial effect: structure of the present invention is simple, easily realizes manufacturing, axial flow and centrifugal-flow compressor is merged into one, have both advantages concurrently.
Accompanying drawing explanation
Fig. 1 is the structural representation of screw axis of the present invention.
Fig. 2 is the structural representation of running shaft of the present invention.
Embodiment
Below in conjunction with accompanying drawing, the present invention is further described.
As shown in Figure 1, 2, a kind of spiral aero gas turbine engine gas compressor, comprise screw axis 1 and running shaft 2, described screw axis 1 comprises compressor blade 3 and hollow shaft 4, described compressor blade 3 is spirality overall structure, described compressor blade 3 is left hand screw or right-hand screw, and the spiral number of turns is 1-50 circle, the edge of described compressor blade 3 is provided with edge strip, angle between described edge strip and compressor blade 3 edge is 0-180 °, and described edge strip continues along the Hand of spiral of compressor blade 3.Described compressor blade 3 integrated setting is at hollow shaft 4 outer wall, and described compressor blade 3 is overall structure with hollow shaft 4, and it is inner that described running shaft 2 is set in hollow shaft 4, and running shaft 2 rotates and drives screw axis 1 to rotate.
Structure of the present invention is simple, easily realizes manufacturing, and axial flow and centrifugal-flow compressor are merged into one, and has both advantages concurrently.
The above is only the preferred embodiment of the present invention; be noted that for those skilled in the art; under the premise without departing from the principles of the invention, can also make some improvements and modifications, these improvements and modifications also should be considered as protection scope of the present invention.
Claims (4)
1. a spiral aero gas turbine engine gas compressor, it is characterized in that: comprise screw axis (1) and running shaft (2), described screw axis (1) comprises compressor blade (3) and hollow shaft (4), described compressor blade (3) is spirality overall structure, the edge of described compressor blade (3) is provided with edge strip, described compressor blade (3) integrated setting is at hollow shaft (4) outer wall, it is inner that described running shaft (2) is set in hollow shaft (4), and running shaft (2) rotates and drives screw axis (1) to rotate.
2. a kind of spiral aero gas turbine engine gas compressor according to claim 1, is characterized in that: described compressor blade (3) is left hand screw or right-hand screw, and the spiral number of turns is 1-50 circle.
3. a kind of spiral aero gas turbine engine gas compressor according to claim 2, it is characterized in that: the angle between described edge strip and compressor blade (3) edge is 0-180 °, and described edge strip continues along the Hand of spiral of compressor blade (3).
4. a kind of spiral aero gas turbine engine gas compressor according to claim 1, is characterized in that: described compressor blade (3) and hollow shaft (4) are overall structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510338686.XA CN104948473A (en) | 2015-06-17 | 2015-06-17 | Spiral compressor for aviation gas turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510338686.XA CN104948473A (en) | 2015-06-17 | 2015-06-17 | Spiral compressor for aviation gas turbine engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104948473A true CN104948473A (en) | 2015-09-30 |
Family
ID=54163418
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510338686.XA Pending CN104948473A (en) | 2015-06-17 | 2015-06-17 | Spiral compressor for aviation gas turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104948473A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2355768A (en) * | 1999-11-01 | 2001-05-02 | Kofi Abaka Jackson | Turbine/compressor rotor with helical blade |
| CN203614428U (en) * | 2013-07-31 | 2014-05-28 | 郭仁发 | Axial-flow fluid pressure machine with spiral blades and turbine |
| CN104370066A (en) * | 2014-11-26 | 2015-02-25 | 天津中外建输送机械有限公司 | Screw conveyer with gradually varied screw pitch |
| CN204783733U (en) * | 2015-06-17 | 2015-11-18 | 南京航空航天大学 | Spiral aviation gas turbine engine compressor |
-
2015
- 2015-06-17 CN CN201510338686.XA patent/CN104948473A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2355768A (en) * | 1999-11-01 | 2001-05-02 | Kofi Abaka Jackson | Turbine/compressor rotor with helical blade |
| CN203614428U (en) * | 2013-07-31 | 2014-05-28 | 郭仁发 | Axial-flow fluid pressure machine with spiral blades and turbine |
| CN104370066A (en) * | 2014-11-26 | 2015-02-25 | 天津中外建输送机械有限公司 | Screw conveyer with gradually varied screw pitch |
| CN204783733U (en) * | 2015-06-17 | 2015-11-18 | 南京航空航天大学 | Spiral aviation gas turbine engine compressor |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20150930 |
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| RJ01 | Rejection of invention patent application after publication |