CN101761395A - Hot gas turbine - Google Patents
Hot gas turbine Download PDFInfo
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- CN101761395A CN101761395A CN200910215114A CN200910215114A CN101761395A CN 101761395 A CN101761395 A CN 101761395A CN 200910215114 A CN200910215114 A CN 200910215114A CN 200910215114 A CN200910215114 A CN 200910215114A CN 101761395 A CN101761395 A CN 101761395A
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- gas turbine
- hot gas
- fuel
- gas compressor
- cold air
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Abstract
The invention relates to a hot gas turbine, which belongs to the technical field of hot gas turbine structures. The hot gas turbine comprises a gas compressor, wherein the gas compressor is connected with driving equipment; rotor vanes and stator vanes are densely distributed in the gas compressor; the output end of the gas compressor is communicated with a cold air channel in which a fuel combustion chamber is arranged; the combustion chamber is provided with a fuel delivery device; the cold air channel is communicated with the hot gas turbine through a fuel gas and cold air mixed hot-gas pipeline; and a speed reducer is arranged between the hot gas turbine and the gas compressor and is connected with a load. The hot gas turbine has the characteristics of rational structural design, low cost, high heat efficiency and durability.
Description
Technical field
The present invention relates to a kind of hot gas turbine, belong to the hot gas turbine technical field of structures.
Background technique
At present, the working principle of conventional art gas turbine is: inhaled air is compressed to the pressure of several kilograms or more than 20 kilogram every square centimeter through gas compressor, enter the burning of firing chamber and fuel mix, high-temperature fuel gas sprays to gas turbine, make the gas turbine generation power that runs up, drive gas compressor work by gas turbine again, simultaneously the outside outputting power of driving mechanism.
There is two large problems in existing gas turbine: 1, cost is high; 2, the thermal efficiency is difficult to further raising, wherein the reason that cost is high is: the high-speed fuel gas that gas-turbine blade is in about 1200 degree washes away down, runs up for a long time, and existing blade material cost is high, also will take complicated blade cooling method, material property is near the limit; The reason that the thermal efficiency is difficult to further improve is: the method that prior art improves the thermal efficiency is to improve gas compressor air pressure, raising fuel gas temperature, limits because of being subjected to material property, has not had potentiality and can dig.
Summary of the invention
The objective of the invention is to solve the deficiency that above-mentioned prior art exists, a kind of reasonable in design is provided, cost is low, thermal efficiency height, long-lived hot gas turbine.
The present invention is achieved through the following technical solutions:
A kind of hot gas turbine, its special way be to comprise with driving arrangement 12 be connected, inside is densely covered with rotor blade 15 and the gas compressor 1 of stator vane 16, the output terminal of gas compressor 1 is connected with the inner cold air channel 5 that is provided with fuel combustion chamber 10, firing chamber 10 is provided with fuel delivery means, cold air channel 5 is connected with hot gas turbine 4 by combustion gas, cool air mixed heat feed channel 11, between hot gas turbine 4 and the gas compressor 1 speed reducer 3 is installed, speed reducer 3 is connected with load 9;
Described speed reducer 3 is connected with hot gas turbine 4, gas compressor 1 by transmission shaft 2;
Described fuel delivery means is the material feeding mouth of being located on the cold air channel 5 17;
Described fuel delivery means comprises the power transmission 13 that is connected with gas compressor 1 output terminal, power transmission 13 drives 8 work of coupled fuel conveyor, fuel conveyor 8 connects by fuel outlet 7 and firing chamber 10, and fuel conveyor 8 is provided with fuel tank 6;
Described cold air channel 5 is provided with combustion residue impurity discharging port 14.
A kind of hot gas turbine of the present invention, reasonable in design, the fuel burner outside is provided with cold air channel, thereby make mixed gas working medium temperature lower, increased the working life of hot gas turbine blade, between gas compressor and the hot gas turbine speed reducer is installed, can reduce the rotating speed of gas compressor greatly, reduce airspeed, thereby make combustion gas that time enough and cool air hybrid cooling be arranged, and the low speed flow flow resistance can reduce, help improving the thermal efficiency, and slow-speed of revolution gas compressor is easy to manufacture, the cost of can demoting significantly.
Description of drawings
Fig. 1: a kind of hot gas turbine embodiment's 1 of the present invention structural representation;
Fig. 2: a kind of hot gas turbine embodiment's 2 of the present invention structural representation;
Fig. 3: the structural representation of gas compressor.
Among the figure: 1, gas compressor, 2, transmission shaft, 3, speed reducer, 4, hot gas turbine, 5, cold air channel, 6, fuel tank, 7, fuel outlet, 8, fuel conveyor, 9, load, 10, firing chamber, 11, combustion gas, cool air mixed gas pipeline, 12, driving arrangement, 13, power transmission, 14, impurity discharging port, 15, rotor blade, 16, stator vane, 17, material feeding mouth.
Embodiment
Provide the embodiment of invention below with reference to accompanying drawing, be used for formation of the present invention is described further.
A kind of hot gas turbine of present embodiment with reference to the accompanying drawings 1,3, comprise with driving arrangement 12 be connected, inside is densely covered with rotor blade 15 and the gas compressor 1 of stator vane 16, the output terminal of gas compressor 1 is connected with the inner cold air channel 5 that is provided with fuel combustion chamber 10, firing chamber 10 is provided with fuel delivery means, cold air channel 5 is connected with hot gas turbine 4 by combustion gas, cool air mixed heat feed channel 11, between hot gas turbine 4 and the gas compressor 1 speed reducer 3 is installed, speed reducer 3 is connected with load 9; Speed reducer 3 is connected with hot gas turbine 4, gas compressor 1 by transmission shaft 2; Fuel delivery means comprises the power transmission 13 that is connected with gas compressor 1 output terminal, power transmission 13 drives 8 work of coupled fuel conveyor, fuel conveyor 8 connects by fuel outlet 7 and firing chamber 10, and fuel conveyor 8 is provided with fuel tank 6; Cold air channel 5 is provided with combustion residue impurity discharging port 14.
Present embodiment and embodiment's 1 difference is that fuel delivery means is the material feeding mouth of being located on the cold air channel 5 17.
Working principle: driving arrangement 12 drives gas compressor 1 work, air enters cold air channel 5 after compression, be provided with fuel combustion chamber 10 in the cold air channel 5, by fuel delivery means fuel is sent into firing chamber 10, fuel will produce high hot combustion gas after the internal combustion of firing chamber, combustion gas with the compression after cool air mix, fuel gas temperature is reduced, combustion gas and cool air are by combustion gas, cool air mixed heat feed channel 11 sprays to hot gas turbine 4, driving hot gas turbine 4 runs up, because mixed gas working medium temperature is lower, thereby increased the working life of hot gas turbine blade, reduce the blade material cost, the hot gas turbine 4 turbines generation power that runs up, drive gas compressor 1 running, be provided with speed reducer 3 between hot gas turbine 4 and the gas compressor 1, make the power of hot gas turbine 4 outputs obtain passing to gas compressor 1 again after the deceleration, can reduce the rotating speed of gas compressor 1 so greatly, reduce airspeed, thereby make combustion gas that time enough and cool air hybrid cooling be arranged, and the low speed flow flow resistance can reduce, help improving the thermal efficiency, because gas compressor 1 inside is densely covered with rotor blade 15 and stator vane 16, thereby has guaranteed enough pressure.
The hot gas turbine of present embodiment to the understanding that improves the thermal efficiency is: the traditional gas turbine and the hot gas turbine of present embodiment all are that air is made conversion of heat into kinetic energy as working medium through heating-expansion-workmanship, in the process of Conversion of energy, there is a The key factor determining the height of Conversion of energy usefulness, be that gas working medium is in heated process, optimal situation is that the density of gas working medium is not less than the natural density before being inhaled into, if the density when heating has reduced, the usefulness of Conversion of energy will reduce, play an analogy, when gas is heated and under the unrestricted situation of volume, volume meeting free expansion, density also decreases, the pressure of this moment is zero, and kinetic energy transforms usefulness and also just equals zero, yet, gas is heated under the situation that density does not reduce, the pressure of the high more generation of temperature is high more, this explanation concern Conversion of energy usefulness principal element just be gas working medium in heated process, whether kept enough density.
A kind of hot gas turbine of present embodiment and the difference of conventional art are, the power of hot gas turbine output slows down through speed reducer, pass to gas compressor, in order to guarantee enough pressure, need to increase compressor blade progression, the air that is compressed by gas compressor, be divided into two kinds of passages, wherein a kind of passage is an air of participating in burning, and another kind of passage is to make cool air and combustion gas mixing, to reach the purpose that reduces temperature, a key character of this technology is: cool air combines with combustion gas, needs the regular hour, reduces the gas compressor rotating speed accordingly, reduce airspeed, can bring following benefit:
1, the gas working medium temperature reduces, thereby the turbine blade material price is reduced, and has effectively saved resource;
2, institute must working pressure also corresponding reduction, thereby the sufficient density when guaranteeing that gas working medium is heated, and the low speed flow flow resistance is low, has improved the thermal efficiency;
3, combustion gas has time enough and cool air hybrid cooling;
4, slow-speed of revolution gas compressor is easy to manufacture, can reduce cost significantly.
Claims (5)
1. hot gas turbine, it is characterized in that comprising with driving arrangement (12) be connected, inside is densely covered with rotor blade (15) and the gas compressor of stator vane (16) (1), the output terminal of gas compressor (1) is connected with the cold air channel (5) that inside is provided with fuel combustion chamber (10), firing chamber (10) is provided with fuel delivery means, cold air channel (5) is connected with hot gas turbine (4) by combustion gas, cool air mixed heat feed channel (11), between hot gas turbine (4) and the gas compressor (1) speed reducer (3) is installed, speed reducer (3) is connected with load (9).
2. according to the described a kind of hot gas turbine of claim 1, it is characterized in that described speed reducer (3) is connected with hot gas turbine (4), gas compressor (1) by transmission shaft (2).
3. according to the described a kind of hot gas turbine of claim 1, it is characterized in that described fuel delivery means is for being located at the material feeding mouth (17) on the cold air channel (5).
4. according to the described a kind of hot gas turbine of claim 1, it is characterized in that described fuel delivery means comprises the power transmission (13) that is connected with gas compressor (1) output terminal, power transmission (13) drives and connects fuel conveyor (8), fuel conveyor (8) connects by fuel outlet (7) and firing chamber (10), and fuel conveyor (8) is provided with fuel tank (6).
5. according to the described a kind of hot gas turbine of claim 1, it is characterized in that described cold air channel (5) is provided with combustion residue impurity discharging port (14).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910215114A CN101761395A (en) | 2009-12-26 | 2009-12-26 | Hot gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910215114A CN101761395A (en) | 2009-12-26 | 2009-12-26 | Hot gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101761395A true CN101761395A (en) | 2010-06-30 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200910215114A Pending CN101761395A (en) | 2009-12-26 | 2009-12-26 | Hot gas turbine |
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| Country | Link |
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| CN (1) | CN101761395A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2616256A (en) * | 1946-09-16 | 1952-11-04 | Babcock & Wilcox Co | Gas turbine plant using solid ash-containing fuel |
| GB835090A (en) * | 1956-09-28 | 1960-05-18 | Daimler Benz Ag | Improvements relating to combustion gas turbine power sets adapted for being alternatively used for braking |
| GB1020131A (en) * | 1962-09-07 | 1966-02-16 | Lucas Industries Ltd | Combustion apparatus |
| CN101280726A (en) * | 2007-04-03 | 2008-10-08 | 通用电气公司 | Power output system and gas turbine assembly including same |
| CN201152198Y (en) * | 2008-01-29 | 2008-11-19 | 马龙根 | Coal fines two-phase stream material feeding device of coal fines gas turbine |
| CN201581995U (en) * | 2009-12-26 | 2010-09-15 | 姜文岐 | Hot-gas turbine |
-
2009
- 2009-12-26 CN CN200910215114A patent/CN101761395A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2616256A (en) * | 1946-09-16 | 1952-11-04 | Babcock & Wilcox Co | Gas turbine plant using solid ash-containing fuel |
| GB835090A (en) * | 1956-09-28 | 1960-05-18 | Daimler Benz Ag | Improvements relating to combustion gas turbine power sets adapted for being alternatively used for braking |
| GB1020131A (en) * | 1962-09-07 | 1966-02-16 | Lucas Industries Ltd | Combustion apparatus |
| CN101280726A (en) * | 2007-04-03 | 2008-10-08 | 通用电气公司 | Power output system and gas turbine assembly including same |
| CN201152198Y (en) * | 2008-01-29 | 2008-11-19 | 马龙根 | Coal fines two-phase stream material feeding device of coal fines gas turbine |
| CN201581995U (en) * | 2009-12-26 | 2010-09-15 | 姜文岐 | Hot-gas turbine |
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Application publication date: 20100630 |