CN104948496A - Spiral turbine of aviation gas turbine engine - Google Patents
Spiral turbine of aviation gas turbine engine Download PDFInfo
- Publication number
- CN104948496A CN104948496A CN201510338215.9A CN201510338215A CN104948496A CN 104948496 A CN104948496 A CN 104948496A CN 201510338215 A CN201510338215 A CN 201510338215A CN 104948496 A CN104948496 A CN 104948496A
- Authority
- CN
- China
- Prior art keywords
- spiral
- shaft
- turbine
- compressor blade
- hollow shaft
- 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
Links
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a spiral turbine of an aviation gas turbine engine. The turbine 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 and 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 turbine 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 turbine.
Background technique
Turbine 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 turbine has two large classes, and one is centrifugal turbine, and single stage supercharging ratio (increasing air flow pressure ratio before and after ratio and turbine) is large, but generally can not exceed two-stage; Another kind is axial-flow turbine, 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 turbine 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 turbine, 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 turbine, comprise screw axis and running shaft, described screw axis comprises compressor blade and hollow shaft, described compressor blade is spirality overall structure, described compressor blade integrated setting is at hollow shaft outer wall, 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, 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.
Be a kind of spiral aero gas turbine engine turbine as shown in Figure 1, 2, 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, described compressor blade 3 integrated setting is at hollow shaft 4 outer wall, described compressor blade 3 is overall structure with hollow shaft 4, 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 (3)
1. a spiral aero gas turbine engine turbine, 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, 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 turbine 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 turbine 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 |
|---|---|---|---|
| CN201510338215.9A CN104948496A (en) | 2015-06-17 | 2015-06-17 | Spiral turbine of aviation gas turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510338215.9A CN104948496A (en) | 2015-06-17 | 2015-06-17 | Spiral turbine of aviation gas turbine engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104948496A true CN104948496A (en) | 2015-09-30 |
Family
ID=54163437
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510338215.9A Pending CN104948496A (en) | 2015-06-17 | 2015-06-17 | Spiral turbine of aviation gas turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104948496A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2355768B (en) * | 1999-11-01 | 2004-03-17 | Kofi Abaka Jackson | Compressor or turbine rotor having spirally curved blades |
| CN102926822A (en) * | 2012-11-13 | 2013-02-13 | 罗士武 | Stepped helical blade for steam turbine, gas turbine and aircraft engine |
| CN203614428U (en) * | 2013-07-31 | 2014-05-28 | 郭仁发 | Axial-flow fluid pressure machine with spiral blades and turbine |
| CN204783815U (en) * | 2015-06-17 | 2015-11-18 | 南京航空航天大学 | Spiral aviation gas turbine engine turbine |
-
2015
- 2015-06-17 CN CN201510338215.9A patent/CN104948496A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2355768B (en) * | 1999-11-01 | 2004-03-17 | Kofi Abaka Jackson | Compressor or turbine rotor having spirally curved blades |
| CN102926822A (en) * | 2012-11-13 | 2013-02-13 | 罗士武 | Stepped helical blade for steam turbine, gas turbine and aircraft engine |
| CN203614428U (en) * | 2013-07-31 | 2014-05-28 | 郭仁发 | Axial-flow fluid pressure machine with spiral blades and turbine |
| CN204783815U (en) * | 2015-06-17 | 2015-11-18 | 南京航空航天大学 | Spiral aviation gas turbine engine turbine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US7144221B2 (en) | Method and apparatus for assembling gas turbine engines | |
| EP2543867B1 (en) | Efficient, low pressure ratio propulsor for gas turbine engines | |
| US8967967B2 (en) | Propfan engine | |
| BR112017006884B1 (en) | AIRCRAFT TURBOMACHINE AND AIRCRAFT TURBOMACHINE STATOR | |
| EP3734052A1 (en) | Efficient, low pressure ratio propulsor for gas turbine engines | |
| CN109854377A (en) | A kind of novel aerial turbo fan engine | |
| CN105864105A (en) | Axial flow compressor stator with in-vitro small blades in hub corner area | |
| JP2017129124A (en) | Method and system for in-line distributed propulsion | |
| CN103573469B (en) | A kind of fan aerodynamic arrangement structures and methods of fanjet | |
| CN107061314A (en) | The low-pressure compressor changed a social system using retired engine | |
| CN204436597U (en) | The low loss of a kind of turbogenerator cooling system is prewhirled gas-supplying structure and turbine rotor cooling flowing path structure thereof | |
| CN204267333U (en) | A kind of high performance of axial flow pump fan | |
| CN105539838A (en) | Automatic variable-pitch propeller and automatic variable-pitch rotorcraft | |
| CN204783815U (en) | Spiral aviation gas turbine engine turbine | |
| CN205331052U (en) | Impeller of organic airfoil fan of counter -rotating fan apparatus | |
| CN204783733U (en) | Spiral aviation gas turbine engine compressor | |
| CN102889237B (en) | Blade wheel with large blades and small blades applying front edges with sharp corners and air compressor | |
| CN104948496A (en) | Spiral turbine of aviation gas turbine engine | |
| CN202991240U (en) | High-rotary-speed and small-size pressure control device of turbine engine | |
| CN203770207U (en) | Fan impeller mechanism | |
| CN103047193B (en) | Surge-preventing structure for aero-engine compressor | |
| CN104948473A (en) | Spiral compressor for aviation gas turbine engine | |
| CN204267382U (en) | A kind of low noise axial fan | |
| CN209621470U (en) | A kind of novel aerial turbo fan engine | |
| US11047393B1 (en) | Multi-stage centrifugal compressor, casing, and return vane |
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 | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20150930 |