CN101699045A - Miniature composite turbine engine - Google Patents
Miniature composite turbine engine Download PDFInfo
- Publication number
- CN101699045A CN101699045A CN200910223429A CN200910223429A CN101699045A CN 101699045 A CN101699045 A CN 101699045A CN 200910223429 A CN200910223429 A CN 200910223429A CN 200910223429 A CN200910223429 A CN 200910223429A CN 101699045 A CN101699045 A CN 101699045A
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- CN
- China
- Prior art keywords
- turbine
- composite turbine
- turbine engine
- tubular type
- 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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- 239000002131 composite material Substances 0.000 title claims abstract description 21
- 238000010304 firing Methods 0.000 claims description 4
- 230000001914 calming effect Effects 0.000 claims description 3
- 239000011148 porous material Substances 0.000 claims description 2
- 239000007789 gas Substances 0.000 abstract description 16
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 abstract description 6
- 239000003345 natural gas Substances 0.000 abstract description 3
- 239000000725 suspension Substances 0.000 abstract description 2
- 239000000446 fuel Substances 0.000 description 2
- 239000002737 fuel gas Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
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- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to a miniature composite turbine engine which combines a centrifugal compressor turbine and an axial gas turbine into one turbine so as to ensure that an engine only has one turbine rotating part. The magnetic suspension bearing support is adopted in the turbine engine of the invention so that the composite turbine can suspend in the air and rotate in high speed to output the mechanical energy. The miniature composite turbine engine can be widely used in fields of energy, aerospace and traffic and is particularly suitable for the heavy vehicle and the power system of the engineering machinery. The turbine engine of the invention can also be used as the prime mover of the burning natural gas distributed power apparatus.
Description
Technical field
The present invention relates to a kind of micro gas turbine engine.Micro gas turbine engine mainly comprises: gas compressor, firing chamber, turbine and annex.Most of micro gas turbine engines adopt centrifugal-flow compressor and centripetal turbine structure.
Background technique
Be further simplified structure, centrifugal compressor turbine and gas turbine are entad cast a turbine, utilize the gas compressor pressurized air of a side, after burning with fuel mix in the firing chamber, drive the entad gas turbine of opposite side, make high engine speeds rotation output mechanical energy.But entad gas turbine efficient is lower, needs further integrated structure, increases work efficiency.
Summary of the invention:
The present invention proposes a kind of new design of micro gas turbine engine basic structure.Be that centrifugal compressor turbine in the micro gas turbine engine and axial gas turbine are combined into a turbine, make micro gas turbine engine have only a turbine revolving part.It is characterized in that: composite turbine adopts centrifugal tubular type turbine blade A, and pore is the channel C of calming the anger of centrifugal compressor, and centrifugal tubular type blade outer wall is an aerodynamic force aerofoil profile profile, forms axial hollow gas-turbine blade.Be the blast tube B of band crownshaft to gas turbine between two centrifugal tubular type turbine blades, centrifugal tubular type blade is the centrifugal compressor blade on the composite turbine, also is axial gas-turbine blade.The pressurized air of composite turbine, through the hollow channel of axial hollow gas-turbine blade, heated compressed air when turbine blade is cooled off has improved the basal temperature of firing chamber, has also improved the preceding fuel gas temperature of turbine simultaneously.Integral body has improved the comprehensive utilization ratio of the energy.
Description of drawings:
Accompanying drawing 1 composite turbine front view
Centrifugal tubular type turbine blade A, the band crownshaft is to gas turbine blast tube B.
Accompanying drawing 2 composite turbine sectional views
Centrifugal tubular type turbine blade A, the band crownshaft is to gas turbine blast tube B.
Accompanying drawing 3 composite turbine A are to unfolded drawing
The channel C of calming the anger of centrifugal compressor
Embodiment:
Miniature composite turbine engine adopts the magnetic suspension bearing supporting, but composite turbine high speed rotating output mechanical energy in air.Miniature composite turbine engine can be widely used in the energy, aviation, and field of traffic etc. especially are fit to heavy vehicle, engineering machinery power system.Also can become prime mover of natural gas fuel burning natural gas distributed power apparatus.
Claims (5)
1. miniature composite turbine engine, by composite turbine, the firing chamber, casing and annex are formed.It is characterized in that having on the composite turbine centrifugal tubular type blade A.
2. the centrifugal tubular type blade A on the described composite turbine of claim 1 is the channel C of calming the anger of centrifugal compressor in the pore.
3. the outer wall of the centrifugal tubular type blade A on the described composite turbine of claim 1 is an aerodynamic force aerofoil profile profile, forms axial hollow gas-turbine blade.
4. on the described composite turbine of claim 1 between two centrifugal tubular type blade A, be the axial blast tube B of band hat.
5. centrifugal tubular type blade A radial equipartition is on composite turbine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910223429A CN101699045A (en) | 2009-11-16 | 2009-11-16 | Miniature composite turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910223429A CN101699045A (en) | 2009-11-16 | 2009-11-16 | Miniature composite turbine engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101699045A true CN101699045A (en) | 2010-04-28 |
Family
ID=42147509
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200910223429A Pending CN101699045A (en) | 2009-11-16 | 2009-11-16 | Miniature composite turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101699045A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108952964A (en) * | 2018-07-13 | 2018-12-07 | 南昌航空大学 | A gas turbine engine with a single compound impeller |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1087405A (en) * | 1992-11-25 | 1994-06-01 | 发动机制造设计局 | The rotor of vane compressor |
| CN2382846Y (en) * | 1999-07-28 | 2000-06-14 | 陶用均 | Centrifugal engine |
-
2009
- 2009-11-16 CN CN200910223429A patent/CN101699045A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1087405A (en) * | 1992-11-25 | 1994-06-01 | 发动机制造设计局 | The rotor of vane compressor |
| CN2382846Y (en) * | 1999-07-28 | 2000-06-14 | 陶用均 | Centrifugal engine |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108952964A (en) * | 2018-07-13 | 2018-12-07 | 南昌航空大学 | A gas turbine engine with a single compound impeller |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C57 | Notification of unclear or unknown address | ||
| DD01 | Delivery of document by public notice |
Addressee: Dong Guoguang Document name: Notification of Passing Preliminary Examination of the Application for Invention |
|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| AD01 | Patent right deemed abandoned |
Effective date of abandoning: 20100428 |
|
| C20 | Patent right or utility model deemed to be abandoned or is abandoned |