CN2174569Y - Shell recoil gas turbine - Google Patents
Shell recoil gas turbine Download PDFInfo
- Publication number
- CN2174569Y CN2174569Y CN 93240152 CN93240152U CN2174569Y CN 2174569 Y CN2174569 Y CN 2174569Y CN 93240152 CN93240152 CN 93240152 CN 93240152 U CN93240152 U CN 93240152U CN 2174569 Y CN2174569 Y CN 2174569Y
- Authority
- CN
- China
- Prior art keywords
- gas
- fuel
- turbine
- blade
- anger
- 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.)
- Expired - Fee Related
Links
- 239000000446 fuel Substances 0.000 claims abstract description 28
- 239000007789 gas Substances 0.000 claims description 23
- 238000010304 firing Methods 0.000 claims description 15
- 230000001914 calming effect Effects 0.000 claims description 10
- 239000000567 combustion gas Substances 0.000 claims description 9
- 239000007921 spray Substances 0.000 claims description 5
- 239000002828 fuel tank Substances 0.000 claims description 2
- 238000002485 combustion reaction Methods 0.000 abstract description 7
- 230000006835 compression Effects 0.000 abstract 1
- 238000007906 compression Methods 0.000 abstract 1
- 239000003570 air Substances 0.000 description 9
- 239000007788 liquid Substances 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 239000012080 ambient air Substances 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 239000002912 waste gas Substances 0.000 description 1
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- Engine Equipment That Uses Special Cycles (AREA)
Abstract
A casing recoil gas turbine is composed of power rotor, compression mechanism, combustion chamber, power disk, stator consisting of fuel nozzle, fuel input channel and ignitor, and features that the axial movement mode of turbine blade as power is changed, the turbine blade is not cooled, and the output power of single engine can be increased.
Description
The utility model relates to a kind of motor, relates in particular to a kind of housing recoil gas-turbine engine.
Existing directly is that the hot machine of fuel has internal-combustion engine, (impeller shaft dynamic formula) gas turbine etc. with liquid or gas.Vibrate greatly during internal-combustion reciprocating-pisto work, the high speed operation difficulty, power per cylinder output is little, use demanded fuel height, the waste gas public hazards are big, and component are many, the precision height, complex structure, cost height, and that impeller shaft dynamic formula gas turbine has is in light weight, and volume is little, and fuel tolerance is strong, public hazards are few, and starting is fast, characteristics such as automaticity height, but the turbine blade cooling difficulty has influenced the raising of unit efficient.
So the purpose of this utility model is made a kind of turbine blade that changed on the basis of the advantage that is keeping gas turbine be the axle flowing mode of power, do not need turbine blade is cooled off the housing recoil gas turbine that the unit output power is improved.
The utility model is achieved in that with power rotor collection gas pressure mechanism, firing chamber power plate be one; Stator is by fuel nozzle, the fuel input channel, and ignition mechanism is formed.Whole concrete structure removes takes out pressurized fuel, and fuel tank and ignition mechanism also have the connection exhaust gas nozzle power plate (14) that is supported by mechanical support frame (13), combuster (3) in the power plate, combuster shell (6) outside the firing chamber outward; The burning that has that communicates with the firing chamber sprays pipeline (2), burning spout (1), and air is pressed into passage (7) and air entry port (15); What have in firing chamber (3) that fuel nozzle (5) links to each other with its nozzle (5) has a fuel inlet pipe (12); The centrifugal blade of calming the anger of the combuster that in power plate, links to each other (4) with power plate; Axle (11) is not arranged in order, bearing (9), belt pulley (10) (or take turns with other) in the outside of fuel inlet pipe (12); Be pressed into the passage place at air the first-stage centrifugal formula blade (8) of calming the anger is arranged.Fuel sprays into the firing chamber by near input nozzle axle center or the axle center.
The utility model is compared its good effect and is with prior art: (1) specific volume is little mutually because the gas pressure mechanism of this device and power plate are become the gas compressor of one and gas turbine and the split of turbine coaxial-type, and power consumption in light weight is little; (2) on structure, kinetic energy dish and exhaust gas nozzle are in ambient air and contact that its heat-resisting degree ratio is in the heat-resisting degree height of totally enclosed gas turbine blades under the condition, because this device radiation is fast; In addition this device have the rotor of special construction and fuel input nozzle axle this just guaranteed that volume is little, high-power characteristics.
Describe the utility model in detail below in conjunction with accompanying drawing.
Fig. 1 is a front view of the present utility model.
Fig. 2 advances the air side sectional view for single face of the present utility model.
Fig. 3 advances the air side sectional view for another embodiment's of the present utility model single face.
The difference of Fig. 2 and Fig. 3 is shown in Fig. 2-3: Fig. 2 is a single arm type, and it is that a sealed whole body is isolated from the outside the firing chamber that the wheel body one side links with axle, and another side is provided with suction port (15), the blade of calming the anger (8), gas-entered passageway (7); Fig. 3 is double-arm, the wheel body two sides all links with axle, the two sides all is provided with suction port (15), the blade (8) of calming the anger, gas-entered passageway (7) and the secondary blade (4) of calming the anger, when fuel is sent into fuel burner (5) from fuel inlet pipe (12) by certain pressure, ejection atomized liquid fuel or gaseous fuel, the starting ignition device is lighted, fuel burns in firing chamber (3), heat expands the burning indoor gas and overflows to suction port and puff prot rapidly, when the gas that expands overflows suction port, to housing do not produce power (the centrifugal blade ordinary circumstance all is designed to straight plate) when the gas that expands when puff prot overflows then housing just produce and ejection gas opposite effect power, the stressed rotation of housing.Fuel is ceaselessly supplied with, active force constantly is applied on the housing, when gyrating with housing, driven the blade rotation of calming the anger of one, calm the anger blade centrifugal action power for but can stop the combustion gas of firing chamber to be overflowed from suction port, but also the air for fuel combustion to be pressed into the firing chamber, to guarantee that the firing chamber normal combustion is the housing normal rotation.
From the reason wheel, the gas turbine of prior art is the high-speed fuel gas promotion blade movement by the nozzle ejection, the energy of nozzle ejection combustion gas can only farthest be converted into output kinetic energy by multistage blade wheel, but can only be less than the kinetic energy of its nozzle ejection combustion gas, yet its combustion gas of wheeled combustion gas recoil power mechanism (promptly this is novel) is to spray from circumference point of contact, power rim tangent direction, the kinetic energy of nozzle combustion gas is opposite with the kinetic energy direction that power plate obtains, equal and opposite in direction.(according to the active force of power conservation, the law of reaction force opposite sign but equal magnitude).Suction port and the air quantity that is pressed into the firing chamber should be more than or equal to the air quantity that sprays into maximum fuel perfect combustion in theory, and the gross area of combustion gas ejection is slightly larger than the into gross area of air scoop.This is novel be exactly a kind of be fuel utilization (housing) backsurging principle with liquid or gas, produce the gas turbine of power by the housing recoil.
The utility model is widely used in industry, traffic, and agricultural, the rotary-type thermal machine of a kind of desirable middle low power in national defence and the people's life, it will replace reciprocating internal combustion engine as further exploitation, become thermal power machinery of new generation.
Claims (3)
1, a kind of housing recoil gas turbine, it comprises takes out pressurized fuel, fuel tank, ignition mechanism, it is characterized in that: it also comprises the connection exhaust gas nozzle power plate (14) that is supported by mechanical support frame (13), combuster (3) in the power plate, its outer combuster shell (6); The combustion gas that has that communicates with the firing chamber sprays pipeline (2), and combustion gas spout (1), air are pressed into passage (7) and air entry port (15); What have in firing chamber (3) that fuel nozzle (5) links to each other with its mouth has a fuel inlet pipe (12); The centrifugal blade of calming the anger of the combuster that in power plate, links to each other (4) with power plate, axle (11) is arranged in order, bearing (9) belt pulley (10) or take turns with other respectively in the outside of fuel inlet pipe (12): being pressed into the passage place at air has the first-stage centrifugal formula blade (8) of calming the anger.
2, gas-turbine as claimed in claim 1 is characterized in that at gas-turbine be power rotor collection gas pressure mechanism, and the firing chamber power plate is an one, and stator is by fuel nozzle, and burning input channel ignition mechanism is formed.
3, gas-turbine as claimed in claim 1, it is characterized in that gas-turbine can divide single arm type and double-arm, it is a sealed whole body that single arm type wheel body one side links with axle, the firing chamber is isolated from the outside, another side is provided with that suction port (15) is calmed the anger blade (8) gas-entered passageway (7) and double-arm wheel body two sides all links with axle, the two sides all is provided with suction port (15), the blade of calming the anger (8), gas-entered passageway (7) and the secondary blade (4) of calming the anger.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 93240152 CN2174569Y (en) | 1993-09-29 | 1993-09-29 | Shell recoil gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 93240152 CN2174569Y (en) | 1993-09-29 | 1993-09-29 | Shell recoil gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2174569Y true CN2174569Y (en) | 1994-08-17 |
Family
ID=33814482
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 93240152 Expired - Fee Related CN2174569Y (en) | 1993-09-29 | 1993-09-29 | Shell recoil gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2174569Y (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103306639A (en) * | 2013-05-31 | 2013-09-18 | 孔祥真 | Turbine heater |
| CN104564423A (en) * | 2013-10-21 | 2015-04-29 | 王秋林 | Run-off ramjet engine |
| CN109236468A (en) * | 2018-11-21 | 2019-01-18 | 北京驰宇空天技术发展有限公司 | A kind of disc type combustion gas wheel turboshaft engine |
| CN109611207A (en) * | 2018-11-21 | 2019-04-12 | 北京驰宇空天技术发展有限公司 | A kind of combustion gas wheel turboshaft engine |
| CN110360133A (en) * | 2019-06-25 | 2019-10-22 | 辽宁福鞍燃气轮机有限公司 | A kind of through-flow structure of gas turbine compressor |
| CN112081684A (en) * | 2019-06-12 | 2020-12-15 | 程浩鹏 | Jet fan engine |
-
1993
- 1993-09-29 CN CN 93240152 patent/CN2174569Y/en not_active Expired - Fee Related
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103306639A (en) * | 2013-05-31 | 2013-09-18 | 孔祥真 | Turbine heater |
| CN103306639B (en) * | 2013-05-31 | 2015-10-07 | 孔祥真 | Turbine heater |
| CN104564423A (en) * | 2013-10-21 | 2015-04-29 | 王秋林 | Run-off ramjet engine |
| CN109236468A (en) * | 2018-11-21 | 2019-01-18 | 北京驰宇空天技术发展有限公司 | A kind of disc type combustion gas wheel turboshaft engine |
| CN109611207A (en) * | 2018-11-21 | 2019-04-12 | 北京驰宇空天技术发展有限公司 | A kind of combustion gas wheel turboshaft engine |
| CN112081684A (en) * | 2019-06-12 | 2020-12-15 | 程浩鹏 | Jet fan engine |
| CN110360133A (en) * | 2019-06-25 | 2019-10-22 | 辽宁福鞍燃气轮机有限公司 | A kind of through-flow structure of gas turbine compressor |
| CN110360133B (en) * | 2019-06-25 | 2020-10-13 | 辽宁福鞍燃气轮机有限公司 | Gas turbine compressor through-flow structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C57 | Notification of unclear or unknown address | ||
| DD01 | Delivery of document by public notice |
Addressee: Li Shunpu Document name: Notice of termination |
|
| C19 | Lapse of patent right due to non-payment of the annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |