CN102900535A - Turbocharging gas turbine - Google Patents
Turbocharging gas turbine Download PDFInfo
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- CN102900535A CN102900535A CN201210322507XA CN201210322507A CN102900535A CN 102900535 A CN102900535 A CN 102900535A CN 201210322507X A CN201210322507X A CN 201210322507XA CN 201210322507 A CN201210322507 A CN 201210322507A CN 102900535 A CN102900535 A CN 102900535A
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- gas
- turbine
- runoff
- gas turbine
- turbosupercharging
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Abstract
The present invention discloses a turbocharging gas turbine, which comprises a runoff impeller aircompressor, a runoff power turbine and a combustion chamber, wherein a compressed gas outlet of the runoff impeller aircompressor is communicated with the combustion chamber, the combustion chamber is communicated with the runoff power turbine, a gas inlet channel of the runoff impeller aircompressor is provided with at least two aircompressors in a series connection manner, each aircompressor and an exhaust turbine forms a transmission connection, the exhaust turbines are arranged on an exhaust channel of the runoff power turbine in a series connection manner, and the runoff power turbine outputs powder to the runoff impeller aircompressor and a load. The turbocharging gas turbine has advantages of high efficiency and low cost.
Description
Technical field
The present invention relates to the heat power field, especially a kind of gas turbine.
Background technique
Tradition large-scale gas turbine power is large, involve great expense, and the micro-gas-turbine engine efficiency is low.Therefore need a kind of gas turbine of invention.
Summary of the invention
In order to address the above problem, the technological scheme that the present invention proposes is as follows:
A kind of turbosupercharging gas turbine, comprise radial-flow impeller gas compressor, runoff power turbine and firing chamber, the pressurized gas outlet of described radial-flow impeller gas compressor is communicated with described firing chamber, described firing chamber is communicated with described runoff power turbine, intake duct series connection at described radial-flow impeller gas compressor arranges at least two gas compressors, each described gas compressor and an exhaust driven gas turbine are in transmission connection, described exhaust driven gas turbine series connection is arranged on the air outlet flue of described runoff power turbine, and described runoff power turbine is to described radial-flow impeller gas compressor and load outputting power.
Described load is made as generator.
Described load is made as vehicle.
Gas communicating passage between two adjacent described gas compressors is established cooler.
Intake duct at described radial-flow impeller gas compressor is established cooler.
The pressure ratio of described radial-flow impeller gas compressor is greater than 2.
The pressure ratio of described gas compressor is greater than 2.
Impeller gas compressor and turbine are widely used in the supercharging of internal combustion engine field, have pressure ratio height, simple in structure, advantage that cost is low, therefore, the inventor thinks, should take full advantage of impeller gas compressor and turbine and be pressure ratio and the low gas turbine supercharging of expansion ratio, thereby gas turbine proficiency is increased substantially.
Among the present invention, so-called " each described gas compressor and an exhaust driven gas turbine are in transmission connection " refers to that described exhaust driven gas turbine is to described gas compressor outputting power.
Principle of the present invention is: utilize the turbo charged principle of reciprocating engine that the power unit that is made of described radial-flow impeller gas compressor, described runoff power turbine and described firing chamber is carried out supercharging, to reach the purpose that improves system effectiveness.
Among the present invention, should according to the known technology in heat energy and power and gas compression field, necessary parts, unit or system be set in the place of necessity.For example, fuel oil supply system, lubrication system are set, and when being necessary set-point ignition system, cooling system etc.
Beneficial effect of the present invention is as follows:
Turbosupercharging gas turbine proficiency disclosed in this invention is high, cost is low.
Description of drawings
Shown in Figure 1 is the structural representation of the embodiment of the invention 1;
Shown in Figure 2 is the structural representation of the embodiment of the invention 2;
Shown in Figure 3 is the structural representation of the embodiment of the invention 3,
Among the figure:
1 radial-flow impeller gas compressor, 2 runoff power turbines, 3 firing chambers, 4 gas compressors, 5 exhaust driven gas turbines, 7 coolers.
Embodiment
Embodiment 1
Turbosupercharging gas turbine as shown in Figure 1, comprise radial-flow impeller gas compressor 1, runoff power turbine 2 and firing chamber 3, the pressurized gas outlet of described radial-flow impeller gas compressor 1 is communicated with described firing chamber 3, the sender property outlet of described firing chamber 3 is communicated with the working medium entrance of described runoff power turbine 2, intake duct series connection at described radial-flow impeller gas compressor 1 arranges two gas compressors 4, each described gas compressor 4 and an exhaust driven gas turbine 5 are in transmission connection, described exhaust driven gas turbine 5 series connection are arranged on the air outlet flue of described runoff power turbine 2,2 pairs of described radial-flow impeller gas compressors 1 of described runoff power turbine and load outputting power, the pressure ratio of described radial-flow impeller gas compressor 1 is greater than 2.
Optionally, also can at least three above gas compressors 4 be set in the intake duct series connection of described radial-flow impeller gas compressor 1, each described gas compressor 4 and an exhaust driven gas turbine 5 are in transmission connection.
Turbosupercharging gas turbine as shown in Figure 2, itself and embodiment's 1 difference is: the gas communicating passage between two adjacent described gas compressors 4 is established cooler 7, and described load is made as generator, and the pressure ratio of described gas compressor 4 is greater than 2.
Turbosupercharging gas turbine as shown in Figure 3, itself and embodiment's 1 difference is: establish cooler 7 at the intake duct of described radial-flow impeller gas compressor 1, described load is made as vehicle.
Obviously, the invention is not restricted to above embodiment, according to known technology and the technological scheme disclosed in this invention of related domain, can derive or association goes out many flexible programs, all these flexible programs also should be thought protection scope of the present invention.
Claims (7)
1. turbosupercharging gas turbine, comprise radial-flow impeller gas compressor (1), runoff power turbine (2) and firing chamber (3), it is characterized in that: the pressurized gas outlet of described radial-flow impeller gas compressor (1) is communicated with described firing chamber (3), described firing chamber (3) is communicated with described runoff power turbine (2), intake duct series connection at described radial-flow impeller gas compressor (1) arranges at least two gas compressors (4), each described gas compressor (4) is in transmission connection with an exhaust driven gas turbine (5), described exhaust driven gas turbine (5) series connection is arranged on the air outlet flue of described runoff power turbine (2), and described runoff power turbine (2) is to described radial-flow impeller gas compressor (1) and load outputting power.
2. turbosupercharging gas turbine as claimed in claim 1, it is characterized in that: described load is made as generator.
3. turbosupercharging gas turbine as claimed in claim 1, it is characterized in that: described load is made as vehicle.
4. turbosupercharging gas turbine as claimed in claim 1, it is characterized in that: the gas communicating passage between adjacent two described gas compressors (4) is established cooler (7).
5. turbosupercharging gas turbine as claimed in claim 1 is characterized in that: establish cooler (7) at the intake duct of described radial-flow impeller gas compressor (1).
6. turbosupercharging gas turbine as claimed in claim 1, it is characterized in that: the pressure ratio of described radial-flow impeller gas compressor (1) is greater than 2.
7. turbosupercharging gas turbine as claimed in claim 1, it is characterized in that: the pressure ratio of described gas compressor (4) is greater than 2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210322507XA CN102900535A (en) | 2011-09-08 | 2012-09-03 | Turbocharging gas turbine |
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110266222.4 | 2011-09-08 | ||
| CN201110266222 | 2011-09-08 | ||
| CN201210322507XA CN102900535A (en) | 2011-09-08 | 2012-09-03 | Turbocharging gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102900535A true CN102900535A (en) | 2013-01-30 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210322507XA Pending CN102900535A (en) | 2011-09-08 | 2012-09-03 | Turbocharging gas turbine |
Country Status (1)
| Country | Link |
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| CN (1) | CN102900535A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103321748A (en) * | 2013-06-19 | 2013-09-25 | 北京理工大学 | Vertical combustion gas turbine |
| CN103775209A (en) * | 2013-02-01 | 2014-05-07 | 摩尔动力(北京)技术股份有限公司 | Pressurized impeller engine |
| CN104234835A (en) * | 2014-09-05 | 2014-12-24 | 胡晋青 | Gas turbine rotor |
| CN104265504A (en) * | 2013-08-07 | 2015-01-07 | 摩尔动力(北京)技术股份有限公司 | Combustion converting engine |
| CN104948300A (en) * | 2015-06-17 | 2015-09-30 | 上海理工大学 | Combustion gas turbine |
| CN108035804A (en) * | 2017-12-05 | 2018-05-15 | 通化师范学院 | Double matter turbine operating pressures increase method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB959336A (en) * | 1961-12-18 | 1964-05-27 | Prvni Brnenska Strojirna Zd Y | Improvements in and relating to combustion gas turbine systems |
| WO1999049222A1 (en) * | 1998-03-20 | 1999-09-30 | Heon Seok Lee | Small turbo compressor |
| CN101187338A (en) * | 2006-11-07 | 2008-05-28 | 通用电气公司 | Systems and methods for power generation with carbon dioxide isolation |
| US20110088399A1 (en) * | 2009-10-15 | 2011-04-21 | Briesch Michael S | Combined Cycle Power Plant Including A Refrigeration Cycle |
-
2012
- 2012-09-03 CN CN201210322507XA patent/CN102900535A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB959336A (en) * | 1961-12-18 | 1964-05-27 | Prvni Brnenska Strojirna Zd Y | Improvements in and relating to combustion gas turbine systems |
| WO1999049222A1 (en) * | 1998-03-20 | 1999-09-30 | Heon Seok Lee | Small turbo compressor |
| CN101187338A (en) * | 2006-11-07 | 2008-05-28 | 通用电气公司 | Systems and methods for power generation with carbon dioxide isolation |
| US20110088399A1 (en) * | 2009-10-15 | 2011-04-21 | Briesch Michael S | Combined Cycle Power Plant Including A Refrigeration Cycle |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103775209A (en) * | 2013-02-01 | 2014-05-07 | 摩尔动力(北京)技术股份有限公司 | Pressurized impeller engine |
| CN103321748A (en) * | 2013-06-19 | 2013-09-25 | 北京理工大学 | Vertical combustion gas turbine |
| CN103321748B (en) * | 2013-06-19 | 2016-03-16 | 北京理工大学 | Verticle gas turbine |
| CN104265504A (en) * | 2013-08-07 | 2015-01-07 | 摩尔动力(北京)技术股份有限公司 | Combustion converting engine |
| CN104265504B (en) * | 2013-08-07 | 2016-08-24 | 摩尔动力(北京)技术股份有限公司 | Turn burn engine |
| CN104234835A (en) * | 2014-09-05 | 2014-12-24 | 胡晋青 | Gas turbine rotor |
| CN104948300A (en) * | 2015-06-17 | 2015-09-30 | 上海理工大学 | Combustion gas turbine |
| CN108035804A (en) * | 2017-12-05 | 2018-05-15 | 通化师范学院 | Double matter turbine operating pressures increase method |
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| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
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Application publication date: 20130130 |