CN109209640A - A kind of gas turbine and method of operation - Google Patents
A kind of gas turbine and method of operation Download PDFInfo
- Publication number
- CN109209640A CN109209640A CN201811120160.4A CN201811120160A CN109209640A CN 109209640 A CN109209640 A CN 109209640A CN 201811120160 A CN201811120160 A CN 201811120160A CN 109209640 A CN109209640 A CN 109209640A
- Authority
- CN
- China
- Prior art keywords
- turbine
- compressor
- gas turbine
- working medium
- free
- 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
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
- F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention relates to gas turbine field, spy is related to a kind of gas turbine and method of operation.The present invention includes core engine and free turbine component, and core engine only switchs two states, output loading is adjusted by adjusting free turbine inlet temperature or improving working medium power density, so that it is high to export average efficiency in the case of making complete machine variable working condition.
Description
Technical field
The present invention relates to gas turbine field, spy is related to a kind of gas turbine and method of operation.
Background technique
Gas turbine (Gas Turbine) is gas continuously to flow as working medium impeller high speed rotation, by fuel
Energy conversion be useful work internal combustion type dynamic power machine, be a kind of rotary vane type Thermal Motor.
Gas turbine structure is most simple, and best embodies out small in size, light-weight, starting specific to gas turbine
Fastly, less with or without series of advantages such as cooling waters.Gas turbine is in working medium and the main flow of combustion gas, only compressor
(Compressor), the gas turbine cycle of this three big component composition of combustion chamber (Combustor) and turbine (Turbine), leads to
Referred to as simple cycle.Most of gas turbines are all made of simple cycle scheme.
Working medium is inhaled from the outside atmospheric environment in compressor, and is allowed to be pressurized by axial-flow compressor step by step compression, simultaneously
Temperature of Working also correspondinglys increase；Compression working medium is pressed to combustion chamber and the fuel of penetrating is mixed and burned the gas for generating high temperature and pressure
Body；Then expansion work in turbine is entered back into, pushes turbine that compressor and external load rotor is driven to rotate together at high speed, is realized
The chemical energy of gas or liquid fuel is partially converted into mechanical work, and exports electric work.The exhaust gas being discharged from turbine drains into greatly
Gas nature heat release.In this way, the chemical energy of fuel is just converted into thermal energy by gas turbine, and partial heat energy is transformed into mechanical energy.
Usually in the gas turbine, compressor is driven by turbine expansion acting, it is the load of turbine.In simple cycle,
The mechanical work that turbine issues has 1/2 to 2/3 or so to be used to drive compressor, remaining 1/3 or so mechanical work is used to drive hair
Motor.
It is low using the gas turbine of simple cycle and the gas turbine of extraction cycle operational efficiency in underload,
Although in underload, operational efficiency increases using the gas turbine of variable working condition design and cold reheat vapor cycle,
But using the gas turbine design difficulty of variable working condition design big, processing cost is high, and control law is complicated；Using a cold reheating
The gas turbine control response of circulation is slow, and structure is complicated.
In addition gas turbine itself can only provide electricity/function and heat, provide if necessary it is cold if need additionally to add other
Equipment such as bromine cooling machine or air conditioner compressed unit are realized.
Meanwhile the prior art there is problems: overall performance presses specified fuel design, can be by replacing combustion chamber
Switch between the fuel type similar in calorific value.Reason is that the flow of compressor and turbine is matched design, when according to height
When the gas turbine of combustion value fuel (such as natural gas) design is using fuel value difference excessive low calorie fuels (such as biogas), such as
Fruit only replaces corresponding combustion chamber in low heat value, it may appear that two kinds as a result, one is in order to reach same turbine inlet temperature (TIT), whirlpool
It takes turns flow and is greater than compressor flow, the back pressure of compressor is excessively high, so that surge occurs for unit, cannot run；Another kind is fuel
Underfed, turbine inlet temperature (TIT) is lower, so that complete machine loop parameter declines, efficiency is reduced.Solution at present matches again
Compressor, turbine and combustion chamber, at high cost, risk is big；Or the gas turbine model of corresponding fuel is bought again.
Summary of the invention
In view of the deficiencies of the prior art, the present invention provides a kind of gas turbine and methods of operation.The present invention includes core
Machine and free turbine component, core engine only switch two states, by adjusting free turbine inlet temperature or improving working medium function
Rate Auto-regulating System of Density of Heavy Medium output loading, so that it is high to export average efficiency in the case of making complete machine variable working condition.
The technical scheme is that a kind of method of operation of gas turbine, it is characterised in that: it is high that compressor exports two-way
Working medium is pressed, first via high-pressure working medium drives main turbines into motion, and main turbine drives compressor rotation, and the second tunnel high-pressure working medium passes through note
Free turbine rotation can be driven after device, free turbine drives load movement by transmission mechanism.
According to a kind of method of operation of gas turbine as described above, it is characterised in that: the note energy device is cooling
Device or the second combustion chamber.
According to a kind of method of operation of gas turbine as described above, it is characterised in that: main turbine output rate is greater than pressure
Mechanism of qi consumes power, and main turbine output rate is less than 1.05 times of compressor consumption power.
According to a kind of method of operation of gas turbine as described above, it is characterised in that: the flow of the second tunnel high-pressure working medium
It is the 20% to 60% of compressor inlet flow.
The invention also discloses a kind of gas turbine, including core engine and free turbine component, core engine include compressor,
Combustion chamber, main turbine, it is characterised in that: compressor exports two-way high-pressure working medium, wherein high-pressure working medium is through combustion chamber and master all the way
Turbine connection, another way high-pressure working medium are sent into free turbine component；Free turbine component includes note energy device, free turbine, bears
It carrying, transmission mechanism, note energy device input port is connect with compressor delivery outlet, and note energy device delivery outlet is connect with free turbine, from
Transmission mechanism is passed through by turbine and load connects, note energy device is cooler or the second combustion chamber.
According to a kind of gas turbine as described above, it is characterised in that: main turbine output rate is greater than compressor and consumes function
Rate, and main turbine output rate is less than 1.05 times of compressor consumption power.
According to a kind of gas turbine as described above, it is characterised in that: the flow of the second tunnel high-pressure working medium be compressor into
The 20% to 60% of mouth flow.
According to a kind of gas turbine as described above, it is characterised in that: the compressor and main turbine are coaxially connected, main
Turbine rotation drives compressor rotation, and compressor delivery outlet is connect with the input port of combustion chamber and note energy device.
According to a kind of gas turbine as described above, it is characterised in that: the compressor or turbine of core engine are set as N grades, N
Grade compressor and N grades of turbines are used coaxially arranged or are arranged using split axle, and N is more than or equal to 2.
According to a kind of gas turbine as described above, it is characterised in that: inter cooler is arranged between the compressor of core engine.
According to a kind of gas turbine as described above, it is characterised in that: the extraction location of the second tunnel high-pressure working medium is to calm the anger
The interstage locations of machine are drawn simultaneously from the multiple and different positions of compressor.
According to a kind of gas turbine as described above, it is characterised in that: combustion chamber is arranged between the turbine of core engine.
According to a kind of gas turbine as described above, it is characterised in that: including multiple free turbine components, multiple free vortexes
Wheel assembly is arranged in juxtaposition；Or free turbine component includes multiple note energy devices, multiple note energy device tandem workings.
According to a kind of gas turbine as described above, it is characterised in that: including multiple cores machine, multiple cores machine cloth arranged side by side
It sets.
The beneficial effects of the present invention are: 1, core engine only switchs two states, by adjusting free turbine inlet temperature
Output loading is adjusted, average efficiency height is exported in the case of complete machine variable working condition, when load range changes between 50%~110%,
Efficiency change < 2%；Rapidly, control logic is simple for the response of the device of the invention system.2, can generate simultaneously it is hot and cold, electric, one
As existing gas turbine technology can only generate heat and electricity.3, core engine design difficulty reduces.Core engine only has two kinds of shapes of switch
State, adjust combustion engine load be by adjust free turbine import Temperature of Working realize, therefore the compressor of core engine, turbine and
Combustion chamber operates in always projected working point, so only needing to consider that the performance of design point is optimal；Compare existing combustion engine side
Case, the compressor in load variations, turbine, the flow of combustion chamber, pressure, the conditions such as temperature all change, therefore design
When be also contemplated that matching properties when deviateing design point, stability, efficiency etc., so by comparison, the core of this patent
Scheming design only needs to consider the best performance of design point operating condition and becomes the design point operating condition in season, and traditional combustion engine scheme needs
Consider performance under design point operating condition and with the varying load condition in the case of design point inlet temperature, becomes season operating condition and change
Varying load condition under seasonal conditions.4, free turbine design difficulty reduces, and free turbine is according to the variation inlet temperature of load
It changes, but flow and pressure still keep stable, therefore for design, need to pursue is in firm discharge
Under the premise of the work of pressure, how to make the efficiency highest in different temperature, and for traditional combustion engine, for acting
Turbine, the flow of import, pressure, temperature can all change with the variation of load, equally pursue efficient design difficulty much
Greater than this patent.5, when lower heat of combustion fuel, it is only necessary to corresponding combustion chamber is replaced, when combustion engine works normally room, compressor
Inlet flow rate it is still constant, but due to the presence of pressure-regulating device, when temperature reaches design value before main turbine inlet, pressure
Mechanism of qi enters the decline of flow all the way of the combustion chamber of main turbine, and compressor back pressure Auto-matching to design value is fired by main turbine
Flow is identical as main turbine design flow after burning room；The flow of freedom of entry turbine assembly increases, in order to guarantee the stabilization of unit
Operation, free turbine combustor fuel-flow rate is insufficient, guarantees that the back pressure of compressor is in by reducing free turbine inlet temperature
Design value.Although the output power of complete machine is lower than the case where using ideal fuels and respective combustion chamber, the pressure ratio of core engine
All guarantee with main turbine inlet temperature (TIT) identical with primary standard fuel scheme, efficiency also can be identical.To sum up, advantage is modification combustion
Material scheme is simple, at low cost, and risk is small, fuel wide adaptation range.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of apparatus of the present invention.
Fig. 2 is the structural schematic diagram of another embodiment of apparatus of the present invention.
Fig. 3 is the structural schematic diagram of another embodiment of apparatus of the present invention.
Fig. 4 is the structural schematic diagram of another embodiment of apparatus of the present invention.
Fig. 5 is the structural schematic diagram of another embodiment of apparatus of the present invention.
Fig. 6 is the structural schematic diagram of another embodiment of apparatus of the present invention.
Detailed description of the invention: core engine 1, compressor 11, two-stage compressor 11A, combustion chamber 12, secondary combustion chamber 12A, main turbine
13, the main turbine 13A of second level, heat exchanger 14, inter cooler 15, free turbine component 2, note can device 21, cooler 21A, the second combustions
Burn room 21B, free turbine 22, load 23, transmission mechanism 24.
Specific embodiment
Name Resolution: note can inject the energy for device, enable devices to rotation acting.
Technical solution of the present invention is described further below in conjunction with attached drawing.
As shown in Figure 1, a kind of gas turbine of the present invention, including core engine 1 and free turbine component 2, core engine 1 include pressure
Mechanism of qi 11, combustion chamber 12, main turbine 13, free turbine component 2 include that note can device 21, free turbine 22, load 23, driver
Structure 24.
As shown in Figure 1, compressor 11 of the invention and main turbine 13 are coaxially connected, the main rotation of turbine 13 drives compressor 11
Rotation, 11 delivery outlet of compressor are connect with the input port of combustion chamber 12 and note energy device 21.It is high to export two-way for compressor 11 in this way
Working medium is pressed, wherein high-pressure working medium is connect through combustion chamber 12 with main turbine 13 all the way, another way high-pressure working medium is sent into free turbine group
Part 2.
As shown in Figure 1, free turbine component 2 of the invention includes that note can device 21, free turbine 22, load 23, transmission
Mechanism 24, note energy 21 input port of device are connect with 11 delivery outlet of compressor, and note energy 21 delivery outlet of device is connect with free turbine 22,
Free turbine 22 is connect by transmission mechanism 24 with load 23.21 device of note energy device of the invention can for cooler 21A or
Second combustion chamber 21B.Working medium towards free turbine component is heated using the second combustion chamber 21B mode, total amount is light, small in size,
It is compact-sized.Cooler 21A is cooling using spray injection mode, using the cooling work for leading to free turbine 22 of spray injection mode
Matter, while working medium power density is improved, improve free turbine component acting ability.
As described in Figure 2, free turbine component 2 of the invention may include cooler 21A or the second combustion chamber 21B, cooling
Device 21A is connect with the high-pressure working medium delivery outlet of compressor 11, and the second combustion chamber 21B is arranged in cooler 21A and free turbine 22
Between, working medium power density is improved in this way, improves free turbine component acting ability, and keep device total amount light, small in size,
It is compact-sized.
In the present invention, the 20% to 60% of 11 inlet flow rate of compressor flows into note energy device 21, and such as entering note can device 21
Gas flow can be 30%, 35%, 40%, 45%, 50%, 55%, preferred scope can mention in this way 40% to 50%
Height output average efficiency is high, makes efficiency change < 1%.
The invention also discloses a kind of method of operation of gas turbine, the compressor 11 of gas turbine exports two-way high pressure work
Matter, first via high-pressure working medium drive main turbine 13 to move, and main turbine 13 drives compressor 11 to rotate, and the second tunnel high-pressure working medium passes through
Note can drive free turbine 22 to rotate after device 21, and free turbine 22 is moved by the driving of transmission mechanism 24 load 23, and note can fill
Setting 21 can be cooler 21A or the second combustion chamber 21B.
The flow of the present invention preferably the second tunnel high-pressure working medium is the 20% to 60% of 11 inlet flow rate of compressor, preferred scope
40% to 50%, output average efficiency height can be improved in this way, make efficiency change < 1%.
In the present invention, main 13 output power of turbine is greater than compressor 11 and consumes power, and preferably main 13 output power of turbine is small
1.05 times of power are consumed in compressor 11.In this way in the present invention, ability consumed by core engine 1 is lower, is conducive to promote this
Invention fuel utilization efficiency.
Transmission mechanism 24 of the invention can be high-speed coupling acceleration and deceleration case or high-speed coupling.Note energy of the invention
Device 21 can cool down or heat high-pressure working medium, to adjust 22 inlet temperature of free turbine.Load 23 of the invention can be with
For generator, high-speed engine or the mechanism for needing rotating machinery power input.Free turbine component 2 of the invention in this way can be with
It generates thermal energy, electric energy or freezes to the working medium of note energy device 21.
As shown in figure 3, the present invention can also include heat exchanger 14, the setting of heat exchanger 14 compressor 11 and combustion chamber 12 it
Between, main 13 delivery outlet of turbine is connect with 14 input port of heat exchanger, and the heat that turbine 13 main in this way generates can be to compressed work
Matter is preheated, and core engine efficiency is further increased.
As shown in figure 5, multiple cores machine 1 can be arranged in juxtaposition by the present invention, by multiple free turbine components 2 cloth arranged side by side
It sets.2 core engines 1 are arranged in juxtaposition in Fig. 5,3 free turbine components 2 are arranged in juxtaposition.It can also be according to the actual situation by 4 cores
Scheming 1 is arranged in juxtaposition, and 4 free turbine components 2 are arranged in juxtaposition.Due to core engine 1 each in the present invention, free turbine component 2
Independent operating influences smaller, it is possible to have the core engine and/or free vortex of respective combustion chamber by handover configurations between each other
Wheel assembly achievees the purpose that using fuel gas with low heat value.
The present invention can be using the fuel of the method lower heat of combustion of replacement combustion chamber 12, such as biogas, coal bed gas, height
Producer gas, rubbish landfill gas etc..
As shown in figure 4, multiple free turbine components 2 can be arranged in juxtaposition by the present invention, average efficiency can be widened in this way
High combustion engine loading range；Or different free turbine components realize different functions.In Fig. 4, certain free turbine group all the way
The power supply of part 2, the thermal efficiency are high, and cooling supply, the electrical efficiency of another way free turbine component 2 are high, are realized by simple valve transfer
The high-efficient demand of different function.
As shown in Figure 5 and Figure 6, multistage compressor can be set in core of the invention machine 1；It can preferably add in compressor
Inter cooler is added to reduce the wasted work of compressor；As Fig. 6 adds inter cooler 15 between compressor 11, two-stage compressor 11A.The present invention
The extraction location of the second tunnel high-pressure working medium can not be the outlet of compressor, can also be in the interstage locations of compressor, can also
To be from the multiple and different positions of compressor while to draw.Main turbine of the invention can be multistage turbine, as wrapped in Fig. 5 and Fig. 6
Main turbine 13 and the main turbine 13A of second level are included, and reheat machine can be added between multistage turbine, is improved efficiency；As increased in Fig. 6
Secondary combustion chamber 12A.Multistage compressor and multistage turbine of the invention can be using coaxially arranged scheme or using split axle
Arrangement；Multistage compressor and multistage turbine can be three-level or level Four, can design according to the actual situation.
Core of the invention machine 1 is in steady-working state, and operating parameter remains unchanged, and guarantees that overall efficiency is stablized.This
The quick adjusting of output load is realized in invention by adjusting 22 inlet temperature of free turbine, and stabilised efficiency range is wide, and response is fast.
Gas turbine working principle of the invention is as follows: core engine 1 completes start-up course and reaches volume by jiggering, igniting
After determining revolving speed, core engine 1 reaches design work state, and output reaches pressure all the way, the working medium of flow of design parameter, the working medium
The acting of free turbine 22 can be entered after device 21 by note；When combustion engine load variations, the operating parameter of core engine 1 does not become
Change, only adjusts expansion work size by adjusting the temperature of 22 working medium of freedom of entry turbine, and during adjusting temperature, lead to
The flow and pressure for crossing the working medium all the way of free turbine 22 are constantly in stationary value, because core engine 1 is constantly in stable state.When certainly
By the note energy device 21 on 22 1 tunnel of turbine do not exchange heat either realize heating function when, working medium by free turbine 22 acting after,
Delivery temperature is higher than environment temperature, and the exhaust of core engine 1 and the exhaust of free turbine 22 can be used as heat source, and free turbine 22 goes out
Function generates electricity or drives other loads, and combustion engine is in electricity, hot alliance state；When note energy device 21 realizes refrigerating function, working medium is passed through
Temperature can be lower than environment temperature after free turbine 22 expands, and in this state, the exhaust of core engine 1 can be used as heat source, from
Cold source can be used as by the exhaust of turbine 22, free turbine 22 drives electrical power generators or drives required load, at this time
Combustion engine is in electricity, heat, cold triple supply state.
The mountable pressure-regulating device on the downstream pipe after compressor 11, two-way power pressure when guaranteeing to adjust operating condition
It keeping stablizing, pressure-regulating device both may be mounted at main turbine 13 on the way, and also may be mounted at free turbine 22 on the way,
Can also 22 liang of roads of main turbine 13 and free turbine all install.Pressure-regulating device can be pressure-regulating valve, adjustable nozzle
Ring etc. adjusts pressure mechanism and realizes the function.
Claims (14)
1. a kind of method of operation of gas turbine, it is characterised in that: compressor exports two-way high-pressure working medium, first via high-pressure working medium
Main turbines into motion is driven, main turbine drives compressor rotation, and the second tunnel high-pressure working medium can drive free turbine after device by note
Rotation, free turbine drive load movement by transmission mechanism.
2. a kind of method of operation of gas turbine according to claim 1, it is characterised in that: the note energy device is cold
But device or the second combustion chamber.
3. a kind of method of operation of gas turbine according to claim 1 or 2, it is characterised in that: main turbine output rate
Power is consumed greater than compressor, and main turbine output rate is less than 1.05 times of compressor consumption power.
4. a kind of method of operation of gas turbine according to claim 1 or 2, it is characterised in that: the second tunnel high-pressure working medium
Flow be compressor inlet flow 20% to 60%.
5. a kind of gas turbine, including core engine and free turbine component, core engine includes compressor, combustion chamber, main turbine,
Be characterized in that: compressor exports two-way high-pressure working medium, wherein high-pressure working medium is connect through combustion chamber with main turbine all the way, the second tunnel is high
Working medium is pressed to be sent into free turbine component；Free turbine component includes note energy device, free turbine, load, transmission mechanism, and note can fill
It sets input port to connect with compressor delivery outlet, note energy device delivery outlet is connect with free turbine, and free turbine passes through transmission mechanism
It is connected with load, note energy device is cooler or the second combustion chamber.
6. a kind of gas turbine according to claim 5, it is characterised in that: main turbine output rate is consumed greater than compressor
Power, and main turbine output rate is less than 1.05 times of compressor consumption power.
7. a kind of gas turbine according to claim 5 or 6, it is characterised in that: the flow of the second tunnel high-pressure working medium is pressure
The 20% to 60% of mechanism of qi inlet flow rate.
8. a kind of gas turbine according to claim 5 or 6, it is characterised in that: the compressor and main turbine are coaxial
Connection, main turbine rotation drive compressor rotation, and compressor delivery outlet is connect with the input port of combustion chamber and note energy device.
9. a kind of gas turbine according to claim 5 or 6, it is characterised in that: the compressor or turbine of core engine are arranged
It is N grades, N grades of compressors and N grades of turbines are used coaxially arranged or arranged using split axle, and N is more than or equal to 2.
10. a kind of gas turbine according to claim 9, it is characterised in that: cold between being arranged between the compressor of core engine
Device.
11. a kind of gas turbine according to claim 9, it is characterised in that: the extraction location of the second tunnel high-pressure working medium is
The interstage locations of compressor are drawn simultaneously from the multiple and different positions of compressor.
12. a kind of gas turbine according to claim 9, it is characterised in that: combustion chamber is arranged between the turbine of core engine.
13. a kind of gas turbine according to claim 5 or 6, it is characterised in that: more including multiple free turbine components
A free turbine component is arranged in juxtaposition；Or free turbine component includes multiple note energy devices, multiple note energy device tandem workings.
14. a kind of gas turbine according to claim 5 or 6, it is characterised in that: including multiple cores machine, multiple cores
Machine is arranged in juxtaposition.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811120160.4A CN109209640A (en) | 2018-09-25 | 2018-09-25 | A kind of gas turbine and method of operation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811120160.4A CN109209640A (en) | 2018-09-25 | 2018-09-25 | A kind of gas turbine and method of operation |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109209640A true CN109209640A (en) | 2019-01-15 |
Family
ID=64981400
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811120160.4A Pending CN109209640A (en) | 2018-09-25 | 2018-09-25 | A kind of gas turbine and method of operation |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109209640A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110529251A (en) * | 2019-08-22 | 2019-12-03 | 中国人民解放军陆军航空兵学院 | A kind of parallel combustion chambers turboaxle motor |
| CN111794859A (en) * | 2020-06-23 | 2020-10-20 | 北京黄铉动力科技有限公司 | Turbine compressed air engine |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5137230A (en) * | 1991-06-04 | 1992-08-11 | General Electric Company | Aircraft gas turbine engine bleed air energy recovery apparatus |
| US20100003148A1 (en) * | 2007-07-30 | 2010-01-07 | Hispano Suiza | Assistance and emergency backup for the electrical drive of a fuel pump in a turbine engine |
| CN104343538A (en) * | 2013-07-25 | 2015-02-11 | 波音公司 | Bleed air systems for use with aircrafts and related methods |
| CN105626266A (en) * | 2016-01-12 | 2016-06-01 | 中国科学院工程热物理研究所 | Anti-surge air escape energy recycling system of gas turbine |
| CN209011954U (en) * | 2018-09-25 | 2019-06-21 | 杭州螺旋新能源科技有限公司 | A kind of gas turbine |
-
2018
- 2018-09-25 CN CN201811120160.4A patent/CN109209640A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5137230A (en) * | 1991-06-04 | 1992-08-11 | General Electric Company | Aircraft gas turbine engine bleed air energy recovery apparatus |
| US20100003148A1 (en) * | 2007-07-30 | 2010-01-07 | Hispano Suiza | Assistance and emergency backup for the electrical drive of a fuel pump in a turbine engine |
| CN104343538A (en) * | 2013-07-25 | 2015-02-11 | 波音公司 | Bleed air systems for use with aircrafts and related methods |
| CN105626266A (en) * | 2016-01-12 | 2016-06-01 | 中国科学院工程热物理研究所 | Anti-surge air escape energy recycling system of gas turbine |
| CN209011954U (en) * | 2018-09-25 | 2019-06-21 | 杭州螺旋新能源科技有限公司 | A kind of gas turbine |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110529251A (en) * | 2019-08-22 | 2019-12-03 | 中国人民解放军陆军航空兵学院 | A kind of parallel combustion chambers turboaxle motor |
| CN111794859A (en) * | 2020-06-23 | 2020-10-20 | 北京黄铉动力科技有限公司 | Turbine compressed air engine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP4923014B2 (en) | 2-shaft gas turbine | |
| CN103452671B (en) | GTC entrance pressurizes and flow control system | |
| CN104373164B (en) | A kind of IGCC electric power station system with HRSG with Supplementary Firing and method of work | |
| US20110210555A1 (en) | Gas turbine driven electric power system with constant output through a full range of ambient conditions | |
| CN104675680A (en) | Compressed air energy storing system for cold and heat power supply | |
| CN104879177A (en) | Organic Rankin cycle and heat pump cycle coupling system | |
| CN206785443U (en) | A kind of high-pressure natural gas cogeneration distributed energy resource system | |
| US20100175385A1 (en) | Method for Increasing Turndown Capability in an Electric Power Generation System | |
| CN103527320A (en) | Stand-by operation of a gas turbine | |
| CN107288758B (en) | A kind of the combination gas jet power unit and conversion method of split axle | |
| CN113202582B (en) | Compressed air-fuel gas reheating type combined cycle power generation system and method | |
| CN105849370B (en) | The two-spool industrial gas turbine engine of high-pressure ratio | |
| WO2019200975A1 (en) | Heavy-duty gas turbine having variable-speed synchronous motor driven compressor | |
| CN103775211A (en) | Distribution type combined cooling, heating and power supply system for active regulation-control type combustion gas turbine | |
| CN207647562U (en) | A kind of cold and hot, electric, steam co-feeding system | |
| CN104863713B (en) | A kind of auxiliary power unit of integrated offer gases at high pressure | |
| CN109209640A (en) | A kind of gas turbine and method of operation | |
| CN109441634A (en) | A kind of gas turbine and method of operation | |
| CN209011954U (en) | A kind of gas turbine | |
| CN109113866A (en) | A kind of gas turbine and method of operation | |
| CN209011953U (en) | A kind of gas turbine | |
| CN204200282U (en) | A kind of space division system compression device drive unit | |
| CN209011955U (en) | A kind of gas turbine | |
| CN209308835U (en) | A kind of cold and heat combined supply gas turbine | |
| JPH07332109A (en) | Compressed air storage type power generating plant |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |