CN103790706B - A kind of low-temperature mixed power gas turbine method of work - Google Patents
A kind of low-temperature mixed power gas turbine method of work Download PDFInfo
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- CN103790706B CN103790706B CN201410079951.2A CN201410079951A CN103790706B CN 103790706 B CN103790706 B CN 103790706B CN 201410079951 A CN201410079951 A CN 201410079951A CN 103790706 B CN103790706 B CN 103790706B
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Abstract
The invention discloses a kind of low-temperature mixed power gas turbine and method of work, a kind of low-temperature mixed power gas turbine wherein, comprising: fuel-supply pipe, the first axle connected device, pipeline, firing chamber, liquid air nozzle, gas-turbine, the second axle connected device, air inlet, exhaust section, the 3rd axle connected device and gas compressor; Described fuel-supply pipe connects firing chamber; Described first axle connected device is arranged on the front end of gas compressor; Described air inlet is arranged on the rear end of gas compressor; Described firing chamber is arranged in pipeline; Described liquid air nozzle is arranged on the outlet port near firing chamber in pipeline; Described second axle connected device connects gas compressor gas-turbine; Described 3rd axle connected device is arranged on the rear end of gas-turbine; Described exhaust section is arranged on the front end exit place of gas-turbine.The present invention makes full use of heat energy acting, reduces temperature simultaneously, reduces material technology requirement, saves radiation system, and system complexity declines, improve fuel utilization efficiency.
Description
Technical field
The invention belongs to gas turbine field, be specifically related to a kind of low-temperature mixed power gas turbine and method of work.
Background technique
Gas turbine (GasTurbine) is a kind of rotary power machinery being mechanical work using the gas of continuous-flow as working medium, thermal power transfer.In the main flow of air and combustion gas, only have the gas turbine cycle of this three large parts composition of gas compressor (Compressor), firing chamber (Combustor) and gas-turbine (Turbine), be commonly referred to as simple cycle.Most of gas turbine all adopts simple cycle scheme.Because its structure is the simplest, and best embody out volume specific to gas turbine little, lightweight, start fast, few with or without series of advantages such as cooling waters.
Gas compressor sucks air from ambient atmosphere environment, and compresses step by step through axial-flow compressor and make it supercharging, simultaneously air temperature also corresponding raising; Pressurized air is pressed to firing chamber and burns with the fuel mix that sprays into and generate the combustion gas of High Temperature High Pressure; And then enter into gas-turbine expansion work, promote gas-turbine and drive gas compressor High Rotation Speed together with outer load rotor, the chemical energy achieving gas or liquid fuel is partially converted into mechanical work.The waste gas of discharging from gas-turbine drains into the heat release of air nature.Like this, gas turbine is just heat energy the chemical energy of fuel, again partial heat energy is transformed into mechanical energy.Usually in the gas turbine, gas compressor is driven by gas-turbine expansion work, and it is the load of gas-turbine.In simple cycle, the mechanical work that gas-turbine sends has about 1/2 to 2/3 to be used for driving gas compressor, and remaining mechanical work of about 1/3 is used for output mechanical energy, as driven generator.When gas turbine starts, first needing exterior power, is generally starter belt dynamic pressure mechanism of qi, until when the mechanical work that gas-turbine sends is greater than the mechanical work of gas compressor consumption, extraneous starter motor is threaded off, and gas turbine could self work alone.
Gas turbine is with the gas of continuous-flow for working medium impeller High Rotation Speed, is the internal combustion type dynamic power machine of useful work by the energy conversion of fuel, is a kind of rotary vane type heat engine.Gas turbine can be one to be called widely, basic principle is similar, the combustion gas gas-turbine motor of general indication, typically refer to such as, for boats and ships (Israeli troops combat vessel is main), vehicle (the normally bulky car type can holding combustion gas gas-turbine, tank, engineering vehicle etc.).With the gas-turbine motor difference advanced, be that its gas-turbine is except driving transmission shaft, transmission shaft connects outside the transmission system of vehicle, the propeller cavitation of boats and ships etc. again, also can drive gas compressor in addition.
The working procedure of gas turbine is, gas compressor sucks air continuously and compressed from air; Air after compression enters firing chamber, and the fuel mix after-combustion with spraying into, becomes High Temperature High Pressure high-speed fuel gas, flows into expansion work in combustion gas gas-turbine immediately, promotes gas turbine impeller and rotates together with compressor impeller; The acting ability of the high-temperature fuel gas after heating significantly improves, and thus combustion gas gas-turbine is while drive gas compressor, still has complementary work as the output mechanical work of gas turbine.When gas turbine is by standing start, need with starter motor with rotation, after accelerating to energy independent operating, starter motor is just thrown off.
The working procedure of gas turbine is the simplest, is called simple cycle; In addition, extraction cycle and complex loops is also had.The working medium of gas turbine, from air, finally drains into air again, is open cycle; In addition, working medium is also had to be closed the closed cycle recycled.What gas turbine combined with other heat engines is called combined cycle plant.
Gas turbine is a kind of first and then complicated cooler power mechanized equipment, is typical new and high technology intensive product.As high-tech carrier, gas turbine represents the level of aggregation of how theoretical subject and the development of multiple-project field, is the frontier technology of 21 century.Development integrates the gas turbine industry of new technology, new material, new process, is one of important symbol of national high technology level and scientific and technological strength, has very outstanding strategic position.
Gas turbine, compared with other dynamic power machine, has the advantages such as lightweight, volume is little, startup is fast, good reliability, single-machine capacity large, operate steadily, the life-span is long, easy to maintenance.Therefore, the application prospect of gas turbine is boundless.
The compression ratio of the first gentle gas compressor of combustion gas is two principal elements affecting gas turbine proficiency.Improve combustion gas initial temperature, and corresponding raising compression ratio, gas turbine proficiency can be made to significantly improve.
Summary of the invention
The invention provides a kind of low-temperature mixed power gas turbine method of work, comprise the following steps:
S1, firing chamber is sprayed into after fuel enters, air portion after gas compressor compression boosting is divided and is entered firing chamber and fuel mix, in combustion chambers burn after a certain proportion of gas and fuel mix, part directly walk around outer wall of combustion chamber and fuel combustion complete waste gas mixing, the heat that burning produces makes all air and the complete waste gas of fuel combustion heat up to expand, become high-temperature high-speed airflow;
S2, after the liquid air mixing of high-temperature high-pressure air flow and the ejection of liquid air nozzle, mixed gas temperature declines rapidly, but liquid air is by thermal evaporation expansion, mixed medium is still expanded further, produces more high pressure, the air-flow of lower temperature;
S3, high pressure low temperature air propels gas-turbine works, and rotates, gas expansion, cooling, and pressure release, releases energy, and arrives exhaust section, is discharged to air.
Further, also comprise: described gas-turbine by the 3rd axle connected device outputting power acting, after can be with generator, also can belt wheel ship power axle.
Further, also comprise: described low-temperature mixed power gas turbine connects startup power plant by the first axle connected device.
Further, also comprise: described gas compressor work medium power comes from the second axle connected device, and start-up course medium power comes from the first axle connected device.
Advantage of the present invention:
This Biological process of liquid air is used to absorb heat, physical vapor volumetric expansion is done work, make full use of heat energy to make it to be converted into mechanical energy, reduce temperature simultaneously, reduce material technology requirement, save radiation system, do not need other heat recovery, flue gas heat reutilization system, system complexity decline, fuel utilization efficiency significantly improve; Adopt liquid air harmless to system, environmentally friendly, energy-saving and emission-reduction;
Gas-turbine is static and working state direct temperature excursion is little, and its rotor and stator blade gap need not adjust, and turbine configuration simplifies, efficiency improves;
Improve combustion efficiency, do not improve combustion temperature again, NOx discharged nitrous oxides reduces;
The present invention is used for military field Large-Scale Equipment as tank, warship, helicopter, and because the tail gas of ejection does not have heat of high temperature, infrared characteristic, ultraviolet characteristic significantly weaken, and makes infrared homing weapon cannot locating and tracking, realizes infrared stealth.
Except object described above, feature and advantage, the present invention also has other object, feature and advantage.Below with reference to figure, the present invention is further detailed explanation.
Accompanying drawing explanation
The accompanying drawing forming a application's part is used to provide a further understanding of the present invention, and schematic description and description of the present invention, for explaining the present invention, does not form inappropriate limitation of the present invention.
Fig. 1 is a kind of low-temperature mixed power gas turbine structural representation of the present invention;
Fig. 2 is a kind of low-temperature mixed power gas turbine method of work flow chart of the present invention.
Reference character:
1 be fuel air mouth, 2 first axle connected devices, 3 pipelines, 4 be firing chamber, 6 be liquid air nozzle, 8 be air inlet for gas-turbine, 9 is the second axle connected device, 10,11 for exhaust section, 12 be that the 3rd axle connected device, 13 is for gas compressor.
Embodiment
In order to make object of the present invention, technological scheme and advantage clearly understand, below in conjunction with drawings and Examples, the present invention is further elaborated.Should be appreciated that specific embodiment described herein only in order to explain the present invention, be not intended to limit the present invention.
Embodiment 1
With reference to figure 1, a kind of low-temperature mixed power gas turbine as shown in Figure 1, comprising: fuel-supply pipe 1, first axle connected device 2, pipeline 3, firing chamber 4, liquid air nozzle 6, gas-turbine 8, second axle connected device 9, air inlet 10, exhaust section 11, the 3rd axle connected device 12 and gas compressor 13; Described fuel-supply pipe 1 connects firing chamber 4; Described first axle connected device 2 is arranged on the front end of gas compressor 13; Described air inlet 10 is arranged on the rear end of gas compressor 13; Described firing chamber 4 is arranged in pipeline 3; Described liquid air nozzle 6 is arranged on the outlet port near firing chamber 4 in pipeline 3; Described second axle connected device 9 connects gas compressor 13 gas-turbine 8; Described 3rd axle connected device 12 is arranged on the rear end of gas-turbine 8; Described exhaust section 11 is arranged on the front end exit place of gas-turbine 8.
With reference to figure 2, a kind of low-temperature mixed power gas turbine method of work as shown in Figure 2, comprises the following steps:
S1, firing chamber 4 is sprayed into after fuel enters, air portion after gas compressor 13 compresses boosting is divided and is entered firing chamber 4 and fuel mix, burn in firing chamber 4 after a certain proportion of gas and fuel mix, part directly walk around firing chamber 4 outer wall and fuel combustion complete waste gas mixing, the heat that burning produces makes all air and the complete waste gas of fuel combustion heat up to expand, become high-temperature high-speed airflow;
S2, after the liquid air mixing that high-temperature high-pressure air flow and liquid air nozzle 6 spray, mixed gas temperature declines rapidly, but liquid air is by thermal evaporation expansion, mixed medium is still expanded further, produces more high pressure, the air-flow of lower temperature;
S3, high pressure low temperature air propels gas-turbine 8 works, and rotates, gas expansion, cooling, and pressure release, releases energy, and arrives exhaust section 11, is discharged to air.
Also comprise: described gas-turbine 8 by the 3rd axle connected device 12 outputting power acting, after can be with generator, also can belt wheel ship power axle, also can drive other machinery equipment needing rotation torque power source, as realized the power of helicopter by gearbox.
Also comprise: described low-temperature mixed power gas turbine connects startup power plant by the first axle connected device 2.
Also comprise: described gas compressor 13 medium power that works comes from the second axle connected device 9, and start-up course medium power comes from the first axle connected device 2.
The present invention is except using liquid air, and other environmental protection, cheap liquid also can use, as liquid nitrogen, liquid carbon dioxide, and water.Just consider cost, environmental protection, equipment corrosion, efficiency factor, water problem be vaporization heat too large, have corrosion to gas-turbine, efficiency is low, and it is too many that vaporization heat takes away heat.The medium that focuses on of the present invention absorbs heat, and physical expansion, cooling, pressure is counter to be increased, and does not have corrosivity to system, and therefore, the medium that vaporization heat is little is best.
The present invention adopts liquid air Biological process to absorb calory burning, physical vapor expansion work, making full use of thermal energy is mechanical energy, reduce gas-turbine operating temperature simultaneously, reduce material technology requirement, save radiation system, system complexity declines, improve fuel utilization efficiency, adopt liquid air harmless to system, environmentally friendly, energy-saving and emission-reduction; Gas-turbine is static and trend of work temperature spread excursion is little, and rotor and stator blade gap need not adjust, and gas-turbine efficiency improves; Improve combustion efficiency, need not improve combustion temperature again, NOx discharged nitrous oxides reduces; The present invention is used for military field Large-Scale Equipment as tank, warship, helicopter, and because the tail gas of ejection does not have heat, infrared characteristic, ultraviolet characteristic significantly weaken, and makes infrared homing weapon cannot locating and tracking, realizes infrared stealth.
The foregoing is only preferred embodiment of the present invention, not in order to limit the present invention, within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (4)
1.
a kind of low-temperature mixed power gas turbine method of work, is characterized in that, comprise the following steps:
s1, firing chamber (4) is sprayed into after fuel enters, air portion after gas compressor (13) compression boosting is divided and is entered firing chamber (4) and fuel mix, burn in firing chamber (4) after air after compression and fuel mix in certain proportion, part directly walk around firing chamber (4) outer wall and fuel combustion complete waste gas mixing, the heat that burning produces makes all air and the complete waste gas of fuel combustion heat up to expand, become high-temperature high-speed airflow;
s2, after the liquid air mixing that afore-said hot high velocity air and liquid air nozzle (6) spray, mixed gas temperature declines rapidly, but liquid air is by thermal evaporation expansion, mixed medium is still expanded further, produces more high pressure, the air-flow of lower temperature;
s3, high pressure low temperature air propels gas-turbine (8) rotary work, gas expansion, cooling, pressure release, releases energy, and arrives exhaust section (11), is discharged to air.
2.
low-temperature mixed power gas turbine method of work according to claim 1, is characterized in that, also comprise: described gas compressor (13) work medium power comes from the second axle connected device (9), and start-up course medium power comes from the first axle connected device (2).
3.
low-temperature mixed power gas turbine method of work according to claim 1, is characterized in that, also comprise: described low-temperature mixed power gas turbine connects startup power plant by the first axle connected device (2).
4.
low-temperature mixed power gas turbine method of work according to claim 2, is characterized in that, also comprise: described gas-turbine (8) is done work by the 3rd axle connected device (12) outputting power, after can be with generator, also can belt wheel ship power axle.
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| CN112282940A (en) * | 2020-10-28 | 2021-01-29 | 郭瑞君 | Combustion engine starting device and system |
| CN115523027A (en) * | 2021-12-21 | 2022-12-27 | 梅万伦 | Track blade combustion gas turbine engine |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2482394A (en) * | 1945-02-12 | 1949-09-20 | Edwin T Wyman | Gas turbine |
| US3038308A (en) * | 1956-07-16 | 1962-06-12 | Nancy W N Fuller | Gas turbine combustion chamber and method |
| US4731988A (en) * | 1985-07-30 | 1988-03-22 | Michael Munk | Internal combustion engine system and method with reduced noxious emissions |
| US4773846A (en) * | 1985-07-30 | 1988-09-27 | Michael Munk | Combustion system and method with fog injection and heat exchange |
| US5353585A (en) * | 1992-03-03 | 1994-10-11 | Michael Munk | Controlled fog injection for internal combustion system |
| CN203702343U (en) * | 2014-03-06 | 2014-07-09 | 苟仲武 | Low-temperature hybrid power gas turbine |
-
2014
- 2014-03-06 CN CN201410079951.2A patent/CN103790706B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2482394A (en) * | 1945-02-12 | 1949-09-20 | Edwin T Wyman | Gas turbine |
| US3038308A (en) * | 1956-07-16 | 1962-06-12 | Nancy W N Fuller | Gas turbine combustion chamber and method |
| US4731988A (en) * | 1985-07-30 | 1988-03-22 | Michael Munk | Internal combustion engine system and method with reduced noxious emissions |
| US4773846A (en) * | 1985-07-30 | 1988-09-27 | Michael Munk | Combustion system and method with fog injection and heat exchange |
| US5353585A (en) * | 1992-03-03 | 1994-10-11 | Michael Munk | Controlled fog injection for internal combustion system |
| CN203702343U (en) * | 2014-03-06 | 2014-07-09 | 苟仲武 | Low-temperature hybrid power gas turbine |
Non-Patent Citations (1)
| Title |
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| 《蒸汽回注式燃气轮机的发展及其结构特点》;张文清;《燃气轮机技术》;19901231;第3卷(第4期);第1-5页 * |
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Effective date of registration: 20191122 Address after: 314200 Lin Dai Zhen Hong Ni Zhen Bei, Pinghu City, Jiaxing City, Zhejiang Province Patentee after: ZHEJIANG YUANDA HEAVY FORGING CO.,LTD. Address before: 100190, Beijing, Zhongguancun Academy of Sciences Haidian District South Road, No. 8, Cheung garden, No. 1507 Patentee before: Gou Zhongwu |
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Denomination of invention: A working method of low temperature hybrid gas turbine Effective date of registration: 20210917 Granted publication date: 20160113 Pledgee: Linda Branch of Zhejiang Pinghu Rural Commercial Bank Co.,Ltd. Pledgor: ZHEJIANG YUANDA HEAVY FORGING Co.,Ltd. Registration number: Y2021330001656 |
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Date of cancellation: 20230515 Granted publication date: 20160113 Pledgee: Linda Branch of Zhejiang Pinghu Rural Commercial Bank Co.,Ltd. Pledgor: ZHEJIANG YUANDA HEAVY FORGING CO.,LTD. Registration number: Y2021330001656 |