CN107120189A - A kind of simple cycle gas turbine engine based on rotation detonation combustion - Google Patents
A kind of simple cycle gas turbine engine based on rotation detonation combustion Download PDFInfo
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- CN107120189A CN107120189A CN201710499227.9A CN201710499227A CN107120189A CN 107120189 A CN107120189 A CN 107120189A CN 201710499227 A CN201710499227 A CN 201710499227A CN 107120189 A CN107120189 A CN 107120189A
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- Prior art keywords
- detonation combustion
- compressor
- turbine
- combustion
- rotation detonation
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Classifications
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- 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
- F02C3/32—Inducing air flow by fluid jet, e.g. ejector action
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- 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
- F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
- F02C3/30—Adding water, steam or other fluids for influencing combustion, e.g. to obtain cleaner exhaust gases
- F02C3/305—Increasing the power, speed, torque or efficiency of a gas turbine or the thrust of a turbojet engine by injecting or adding water, steam or other fluids
-
- 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
- F02C7/12—Cooling of plants
- F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
- F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
-
- 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
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/35—Combustors or associated equipment
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides a kind of simple cycle gas turbine engine based on rotation detonation combustion, it includes compressor, rotation detonation combustion room, thermojet detonator, injector, mixing machine, turbine, load, low-temperature receiver.Rotation detonation combustion room is applied to simple cycle gas turbine engine, and ensures the non-overtemperature of working medium at turbine inlet in combustor tail increase mixing machine.The present invention adds the acting ability of combustor exit working medium using the supercharging performance of detonation combustion room is rotated, and temperature, component efficiencies, compressor pressure ratio under the same conditions, make thermal efficiency of cycle of combustion turbine improve 5% 10% at turbine inlet.
Description
Technical field
The present invention relates to gas turbine technology, more particularly to a kind of simple cycle combustion gas wheel based on rotation detonation combustion
Machine.
Background technology
Thermal efficiency of cycle of combustion turbine is to evaluate the main performance indications of gas turbine design technical merit, improves combustion gas
The approach of the turbine thermal efficiency have it is following some：Improve combustion gas initial temperature and coordinate optimum pressure ratio, but limited by turbo blade material
System, the annual average energy of combustion gas initial temperature improves 10 degrees Celsius, and efficiency increase rate is more and more limited；Reduce compressor rate of air sucked in required, be
Carry out that turbine blade cooling, wheel disc and blade root cooling, casing be heat-insulated and axial force balance etc. needs the compressed air consumed big
Account for 20% or so of compressor inlet air capacity, if it is possible to reduce 1% blower outlet rate of air sucked in required, so that it may make combustion gas wheel
Machine cycle efficieny and raising 2% or so more relative than work(；Waste heat is exhausted, combustion turbine exhaustion temperature in 500 degrees centigrades,
The waste heat losses discharged with flue gas substantially accounts for more than the 55% of fuel heating amount, if it is possible to utilize a part of waste heat losses, will
Gas turbine cycle efficiency can be significantly improved；Reduce cycle entropy increase, traditional isobaric combustion process is entropy increasing in Brayton cycle
Maximum thermal procession, the entropy for reducing the thermal procession increases the limitation for receiving isobaric combustion principle, and then limits simple cloth
Thunder cycle combustion turbine efficiency is increased substantially.
Detonation combustion is approximately isochoric combustion, and the increasing of process entropy is smaller, and heat release is fast, discharges low.The form master of detonation engine
There are three kinds：In determine detonation engine, pulse detonation engine and rotation detonation engine.Wherein rotation detonation engine due to
It only needs to once light a fire and working range more wide in range advantage is easier to receive for gas turbine, but detonation combustion room exists
Burnt and unstable under the conditions of high air-fuel ratio, and under the conditions of relatively low air-fuel ratio, detonation combustion room outlet temperature is too high, turbine leaf
Piece can not be born again.
The content of the invention
The brief overview on the present invention is given below, to provide on the basic of certain aspects of the invention
Understand.It should be appreciated that this general introduction is not the exhaustive general introduction on the present invention.It is not intended to determine the pass of the present invention
Key or pith, nor is it intended to limit the scope of the present invention.Its purpose only provides some concepts in simplified form,
In this, as the preamble in greater detail discussed later.
In consideration of it, the invention provides a kind of simple cycle gas turbine engine based on rotation detonation combustion, at least to solve
Detonation combustion room under the conditions of high air-fuel ratio combustion instability and outlet temperature is too high so that turbine under the conditions of relatively low air-fuel ratio
The unaffordable problem of blade.
According to an aspect of the invention, there is provided a kind of simple cycle gas turbine engine based on rotation detonation combustion, base
In the simple cycle gas turbine engine of rotation detonation combustion include compressor, rotation detonation combustion room, injector, mixing machine, turbine,
Load and low-temperature receiver；The arrival end of compressor and the port of export of turbine connect low-temperature receiver respectively；Compressor has three ports of export；Pressure
The entrance point of the first outlet end connection rotation detonation combustion room of mechanism of qi, the port of export connection mixing machine of rotation detonation combustion room
First entrance point；The second outlet end of compressor connects the entrance point of injector, and the of the port of export connection mixing machine of injector
Two entrance points, the port of export of mixing machine connects the first entrance point of turbine；The second of the 3rd port of export connection turbine of compressor
Entrance point；Three ports of export of compressor are used to blower outlet air being divided into three parts：Part I enters rotation detonation
Combustion chamber participates in combustion process；Part II by injector enter in the mixing machine of rotation detonation combustion room afterbody come with
Outlet working medium in rotation detonation combustion room is blended, to realize the cooling to exporting working medium；Part III enters turbine and participates in cold
But process.
Further, low-temperature receiver is atmospheric environment, and cycle fluid is discharged directly to atmospheric environment after turbine expansion acting, pressed
Mechanism of qi sucks air from atmospheric environment.
Further, rotation detonation combustion room is non-lean premixed combustor, is detonated using thermojet detonator, the supply of its fuel
Mode is blended while entering combustion chamber for the partial air of blower outlet in entry of combustion chamber and fuel side.
The simple cycle gas turbine engine based on rotation detonation combustion of the present invention, including compressor, rotation detonation combustion room,
Thermojet detonator, injector, mixing machine, turbine, load, low-temperature receiver, it is characterized in that：Air is divided into three after being compressed through compressor
Point, Part I air enters rotation detonation combustion room and participates in combustion process, and working medium enters mixing machine after burning, with Part II
Air is blended, and is realized and is entered turbine after temperature-fall period；Part III air enters turbine and participates in cooling procedure, final all
Working medium is expelled to air from turbine outlet.
The above-mentioned simple cycle gas turbine engine based on rotation detonation combustion of the present invention, by injector and mixing machine plus
Enter, rotation detonation combustion is applied on simple cycle gas turbine engine, thermal efficiency of cycle of combustion turbine is significantly improved.
In addition, the supercharging performance by rotating detonation combustion room, overcomes the traditional combustion room entropy based on isobaric combustion and increases
Excessive the problem of, the acting ability of combustor exit working medium is added, thermal efficiency of cycle of combustion turbine is significantly improved.
In addition, mixing machine utilizes injector, the work that blower outlet partial air and rotated detonation combustion room are pressurized
Matter is blended, and reduction Temperature of Working enters turbine.
The present invention based on rotation detonation combustion simple cycle gas turbine engine, at turbine inlet temperature, component efficiencies,
Under the same conditions, thermal efficiency of cycle improves 5%-10% to compressor pressure ratio, while also reducing pollutant emission.
The simple cycle gas turbine engine based on rotation detonation combustion of the present invention improves the principle of thermal efficiency of cycle：Traditional letter
Single cycle gas-turbine combustion chamber combustion process is similar to isobaric combustion process, there are about 5% pitot loss, and in isobaric combustion
The increasing of combustion process entropy is too big under mode, is a part for entropy increasing maximum during gas turbine cycle, therefore have lost working medium mistake
Many acting abilities；Detonation combustion is a kind of combustion process for being similar to isochoric combustion, and entropy increasing is smaller than isobaric combustion, and rotates quick-fried
Hong combustion chamber has certain boosting capability, the acting ability of combustor exit working medium is significantly improved, so as to improve combustion gas
Turbine thermal efficiency of cycle.
The rotation detonation combustion room of prior art combustion instability under high air-fuel ratio, but if air-fuel is smaller, can make
It is too high into combustor exit temperature.Can turbine first-stage blade bear so high temperature, and can this is by rotation detonation combustion
Burn the major issue that room is applied in gas turbine.By contrast, the simple cycle combustion of the invention based on rotation detonation combustion
Gas-turbine in rotation detonation combustion room afterbody by increasing injector and mixing machine, by from the partial air injection of blower outlet
Into in the high-pressure working medium of combustor exit, temperature-fall period is realized, pressure-air ginseng is obtained without further increase pressure texture
With the working medium blending procedure of rotation detonation combustion room outlet, the wasted work of compressor is reduced, gas turbine is further increased
Thermal efficiency of cycle.
By the detailed description below in conjunction with accompanying drawing to highly preferred embodiment of the present invention, these and other of the invention is excellent
Point will be apparent from.
Brief description of the drawings
The present invention can be by reference to being better understood, wherein in institute below in association with the description given by accompanying drawing
Have and used same or analogous reference in accompanying drawing to represent same or similar part.The accompanying drawing is together with following
Describe the part for including in this manual and being formed this specification together in detail, and for this is further illustrated
The preferred embodiment of invention and the principle and advantage for explaining the present invention.In the accompanying drawings：
Fig. 1 is the circulation signal for schematically showing the simple cycle gas turbine engine based on rotation detonation combustion of the present invention
Figure；
Fig. 2 is the simple cycle gas turbine engine based on rotation detonation combustion and the simple cycle combustion gas wheel based on isobaric combustion
Machine temperature entropy contrast schematic diagram.
It will be appreciated by those skilled in the art that element in accompanying drawing is just for the sake of showing for the sake of simple and clear,
And be not necessarily drawn to scale.For example, the size of some elements may be exaggerated relative to other elements in accompanying drawing, with
Just it is favorably improved the understanding to the embodiment of the present invention.
Embodiment
The one exemplary embodiment of the present invention is described hereinafter in connection with accompanying drawing.For clarity and conciseness,
All features of actual embodiment are not described in the description.It should be understood, however, that developing any this actual implementation
Many decisions specific to embodiment must be made during example, to realize the objectives of developer, for example, symbol
Those restrictive conditions related to system and business are closed, and these restrictive conditions may have with the difference of embodiment
Changed.In addition, it also should be appreciated that, although development is likely to be extremely complex and time-consuming, but to having benefited from the disclosure
For those skilled in the art of content, this development is only routine task.
Herein, in addition it is also necessary to which explanation is a bit, in order to avoid having obscured the present invention because of unnecessary details, in the accompanying drawings
It illustrate only and according to the closely related apparatus structure of the solution of the present invention and/or process step, and eliminate and the present invention
The little other details of relation.
It is quick-fried based on rotating The embodiment provides a kind of simple cycle gas turbine engine based on rotation detonation combustion
Flash over the simple cycle gas turbine engine of burning include compressor, rotation detonation combustion room, injector, mixing machine, turbine, load and
Low-temperature receiver；The arrival end of compressor and the port of export of turbine connect low-temperature receiver respectively；Compressor has three ports of export；The of compressor
The entrance point of one port of export connection rotation detonation combustion room, the port of export of rotation detonation combustion room connects the first import of mixing machine
End；The second outlet end of compressor connects the entrance point of injector, and the port of export of injector connects the second entrance point of mixing machine,
The port of export of mixing machine connects the first entrance point of turbine；3rd port of export of compressor connects the second entrance point of turbine；Pressure
Three ports of export of mechanism of qi are used to blower outlet air being divided into three parts：Part I enters rotation detonation combustion room and participated in
Combustion process；Part II enters in the mixing machine of rotation detonation combustion room afterbody to fire with rotation detonation by injector
Burn room outlet working medium to be blended, to realize the cooling to exporting working medium；Part III enters turbine and participates in cooling procedure.
Fig. 1 gives the structure of an example of the simple cycle gas turbine engine based on rotation detonation combustion of the present invention
Figure.
As shown in figure 1, in this example, the simple cycle gas turbine engine based on rotation detonation combustion includes compressor, rotation
Turn detonation combustion room, injector, mixing machine, turbine, load and low-temperature receiver.The arrival end of compressor and the port of export of turbine are distinguished
Connect low-temperature receiver.
Compressor has three ports of export；The entrance point of the first outlet end connection rotation detonation combustion room of compressor, rotation
The port of export for turning detonation combustion room connects the first entrance point of mixing machine；The second outlet end of compressor connects the import of injector
End, the port of export of injector connects the second entrance point of mixing machine, and the port of export of mixing machine connects the first entrance point of turbine；Pressure
3rd port of export of mechanism of qi connects the second entrance point of turbine.
Three ports of export of compressor are used to blower outlet air being divided into three parts：Part I enters rotation detonation
Combustion chamber participates in combustion process；Part II by injector enter in the mixing machine of rotation detonation combustion room afterbody come with
Outlet working medium in rotation detonation combustion room is blended, to realize the cooling to exporting working medium；Part III enters turbine and participates in cold
But process.
Wherein, low-temperature receiver is, for example, atmospheric environment, and cycle fluid is discharged directly to atmospheric environment after turbine expansion acting, pressed
Mechanism of qi sucks air from atmospheric environment.
According to a kind of implementation, rotation detonation combustion room is non-lean premixed combustor, is detonated using thermojet detonator, its
Fuel supply mode is blended while entering combustion chamber for the partial air of blower outlet in entry of combustion chamber and fuel side.
The thermodynamic cycle side of the simple cycle gas turbine engine based on rotation detonation combustion of the present invention is described with reference to Fig. 1
Case is：Since cycle fluid enters compressor compression process, 1) compressor compression：Working medium is compressed through compressor, increasing temperature and pressure；
2) detonation combustion is rotated：The working medium that Part I compresses through compressor enters non-premixed rotation detonation combustion room, warp with fuel
Chemical heat release is crossed, the high temperature with high acting ability, high-pressure working medium is produced；3) injection type is blended：Part II is through calming the anger
The working medium of machine compression enters combustor tail mixing machine by injector, is blended with combustor exit HTHP working medium,
HTHP working medium is set to be cooled to the scope that turbine first-stage blade is born；4) turbine expansion does work：Blended through mixing machine
HTHP working medium and the working medium compressed through compressor of Part III expansion work, decrease temperature and pressure in turbine；5) heat release：
Turbine outlet working medium comes back to the initial point of low-pressure compressor compression process to low-temperature receiver heat release.
Fig. 2 gives the simple cycle gas turbine engine based on rotation detonation combustion and the simple cycle combustion based on isobaric combustion
Gas-turbine temperature entropy comparing result.As shown in Figure 2, the simple cycle gas turbine engine of the invention based on rotation detonation combustion is due to quick-fried
Flash over and burn the intrinsic superiority of mode, the entropy increasing less than isobaric combustion process (2) is increased in the entropy of rotation detonation combustion process (2 '),
Loss is smaller, therefore thermal efficiency of cycle is higher.
The simple cycle gas turbine engine based on rotation detonation combustion of the present invention, is drawn by increasing between combustion chamber and turbine
Emitter and mixing machine, reduce turbine inlet Temperature of Working, and rotation detonation combustion is applied on simple cycle gas turbine engine, overcome
The problem of traditional combustion room entropy based on isobaric combustion increases excessive, adds the acting ability of combustor exit working medium, improves
Thermal efficiency of cycle of combustion turbine.
Although describing the present invention according to the embodiment of limited quantity, above description, the art are benefited from
It is interior it is clear for the skilled person that in the scope of the present invention thus described, it can be envisaged that other embodiments.Additionally, it should be noted that
The language that is used in this specification primarily to readable and teaching purpose and select, rather than in order to explain or limit
Determine subject of the present invention and select.Therefore, in the case of without departing from the scope and spirit of the appended claims, for this
Many modifications and changes will be apparent from for the those of ordinary skill of technical field.For the scope of the present invention, to this
The done disclosure of invention is illustrative and not restrictive, and it is intended that the scope of the present invention be defined by the claims appended hereto.
Claims (3)
1. a kind of simple cycle gas turbine engine based on rotation detonation combustion, it is characterised in that described based on rotation detonation combustion
Simple cycle gas turbine engine include compressor, rotation detonation combustion room, injector, mixing machine, turbine, load and low-temperature receiver；
The arrival end of the compressor is connected the low-temperature receiver respectively with the port of export of the turbine；
The compressor has three ports of export；The first outlet end connection of the compressor is described to rotate entering for detonation combustion room
Mouth end, the port of export of the rotation detonation combustion room connects the first entrance point of the mixing machine；The second of the compressor goes out
Mouth end connects the entrance point of the injector, and the port of export of the injector connects the second entrance point of the mixing machine, described
The port of export of mixing machine connects the first entrance point of the turbine；3rd port of export of the compressor connects the of the turbine
Two entrance points；
Three ports of export of the compressor are used to the blower outlet air being divided into three parts：Part I enters described
Rotate detonation combustion room and participate in combustion process；Part II is entered located at rotation detonation combustion room afterbody by injector
Blended in mixing machine with rotation detonation combustion room outlet working medium, to realize the cooling to the outlet working medium；The
Three parts enter the turbine and participate in cooling procedure.
2. the simple cycle gas turbine engine according to claim 1 based on rotation detonation combustion, it is characterised in that described cold
Source is atmospheric environment, and cycle fluid is discharged directly to atmospheric environment after turbine expansion acting, and the compressor is from air
Air is sucked in environment.
3. the simple cycle gas turbine engine according to claim 1 based on rotation detonation combustion, it is characterised in that the rotation
Turn detonation combustion room for non-lean premixed combustor, detonated using thermojet detonator, its fuel supply mode is that the compressor goes out
The partial air of mouth is blended while entering combustion chamber in entry of combustion chamber and fuel side.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710499227.9A CN107120189B (en) | 2017-06-27 | 2017-06-27 | A kind of simple cycle gas turbine engine based on rotation detonation combustion |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710499227.9A CN107120189B (en) | 2017-06-27 | 2017-06-27 | A kind of simple cycle gas turbine engine based on rotation detonation combustion |
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| CN107120189A true CN107120189A (en) | 2017-09-01 |
| CN107120189B CN107120189B (en) | 2018-12-21 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108332975A (en) * | 2018-01-22 | 2018-07-27 | 哈尔滨工程大学 | A kind of 1.5 grades of turbine inside rotating disc cavities flowing heat transfer basic test platforms |
| CN112797442A (en) * | 2019-11-13 | 2021-05-14 | 通用电气公司 | Method and system for rotary detonation combustion |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5634327A (en) * | 1994-12-24 | 1997-06-03 | Asea Brown Boveri Ag | Method of operating a gas-turbine group |
| EP1028230A1 (en) * | 1999-02-09 | 2000-08-16 | ABB Alstom Power (Schweiz) AG | Cooled gas turbine component with adjustable cooling |
| CN1310292A (en) * | 2000-02-25 | 2001-08-29 | 株式会社日立制作所 | Gas turbine |
| CN104204467A (en) * | 2012-03-30 | 2014-12-10 | 阿尔斯通技术有限公司 | Gas turbine with adjustable cooling air system |
| CN105089816A (en) * | 2014-05-12 | 2015-11-25 | 通用电气公司 | Enhanced Turbine Cooling System Using a Blend of Compressor Bleed Air and Ambient Air |
-
2017
- 2017-06-27 CN CN201710499227.9A patent/CN107120189B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5634327A (en) * | 1994-12-24 | 1997-06-03 | Asea Brown Boveri Ag | Method of operating a gas-turbine group |
| EP1028230A1 (en) * | 1999-02-09 | 2000-08-16 | ABB Alstom Power (Schweiz) AG | Cooled gas turbine component with adjustable cooling |
| CN1310292A (en) * | 2000-02-25 | 2001-08-29 | 株式会社日立制作所 | Gas turbine |
| CN104204467A (en) * | 2012-03-30 | 2014-12-10 | 阿尔斯通技术有限公司 | Gas turbine with adjustable cooling air system |
| CN105089816A (en) * | 2014-05-12 | 2015-11-25 | 通用电气公司 | Enhanced Turbine Cooling System Using a Blend of Compressor Bleed Air and Ambient Air |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108332975A (en) * | 2018-01-22 | 2018-07-27 | 哈尔滨工程大学 | A kind of 1.5 grades of turbine inside rotating disc cavities flowing heat transfer basic test platforms |
| CN108332975B (en) * | 2018-01-22 | 2020-07-28 | 哈尔滨工程大学 | 1.5-stage turbine rotating disc cavity flow heat transfer foundation test bed |
| CN112797442A (en) * | 2019-11-13 | 2021-05-14 | 通用电气公司 | Method and system for rotary detonation combustion |
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| Publication number | Publication date |
|---|---|
| CN107120189B (en) | 2018-12-21 |
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