CN107120189B - 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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- CN107120189B CN107120189B CN201710499227.9A CN201710499227A CN107120189B CN 107120189 B CN107120189 B CN 107120189B CN 201710499227 A CN201710499227 A CN 201710499227A CN 107120189 B CN107120189 B CN 107120189B
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- detonation combustion
- compressor
- rotation detonation
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- combustion
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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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
The present invention provides a kind of simple cycle gas turbine engines based on rotation detonation combustion, it includes compressor, rotation detonation combustion room, thermojet detonator, injector, mixing machine, turbine, load, cold source.Rotation detonation combustion room is applied to simple cycle gas turbine engine, and increases mixing machine in combustor tail and guarantees the non-overtemperature of working medium at turbine inlet.The present invention increases the acting ability of combustor exit working medium, temperature, component efficiencies, compressor pressure ratio under the same conditions, make thermal efficiency of cycle of combustion turbine improve 5%-10% at turbine inlet using the supercharging performance of rotation detonation combustion room.
Description
Technical field
The present invention relates to gas turbine technology more particularly to a kind of simple cycle combustion gas wheels based on rotation detonation combustion
Machine.
Background technique
Thermal efficiency of cycle of combustion turbine is to evaluate the main performance indicator of gas turbine design technical level, improves combustion gas
The approach of the turbine thermal efficiency has the following: it improves combustion gas initial temperature and cooperates optimum pressure ratio, however by the limit of turbo blade material
System, the every annual of combustion gas initial temperature can improve 10 degrees Celsius, and efficiency increase rate is more and more limited；Reduce compressor sucking rate, is
It carries out turbine blade cooling, wheel disc and blade root is cooling, casing is heat-insulated and the compressed air of the needs consumption such as axial force balance is big
Account for about 20% or so of compressor inlet air capacity, if it is possible to reduce by 1% blower outlet sucking rate, so that it may make combustion gas wheel
Machine cycle efficieny and raising 2% or so more opposite than function；Be exhausted waste heat, combustion turbine exhaustion temperature in 500 degrees centigrades,
55% or more of fuel heating amount is substantially accounted for the waste heat losses that flue gas is discharged, if it is possible to a part of waste heat losses is utilized, it will
Gas turbine cycle efficiency can be significantly improved；Reduce cycle entropy increase, traditional isobaric combustion process is that Brayton cycle medium entropy increases
Maximum thermal procession, the entropy increasing for reducing the thermal procession receives the limitation of isobaric combustion principle, and then limits simple cloth
Thunder cycle combustion turbine efficiency increases substantially.
Detonation combustion is approximately isochoric combustion, and the increasing of process entropy is smaller, and heat release is fast, is discharged low.The form master of detonation engine
Will there are three types of: stay determine detonation engine, pulse detonation engine and rotate detonation engine.Wherein rotation detonation engine due to
It is that gas turbine receives, however detonation combustion room exists that it, which only needs the advantage once lighted a fire and working range is more wide in range to be easier,
It burns under the conditions of high air-fuel ratio and unstable, and under the conditions of lower air-fuel ratio, detonation combustion room outlet temperature is excessively high, turbine leaf
Piece is again unbearable.
Summary of the invention
It has been given below about brief overview of the invention, in order to provide about the basic of certain aspects of the invention
Understand.It should be appreciated that this summary is not an exhaustive overview of the invention.It is not intended to determine pass of the invention
Key or pith, nor is it intended to limit the scope of the present invention.Its purpose only provides certain concepts in simplified form,
Taking this as a prelude to a more detailed description discussed later.
In consideration of it, the present invention provides a kind of simple cycle gas turbine engines 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 excessively high so that turbine under the conditions of lower air-fuel ratio
The unbearable 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 rotation detonation combustion simple cycle gas turbine engine include compressor, rotation detonation combustion room, injector, mixing machine, turbine,
Load and cold source；The arrival end of compressor and the outlet end of turbine are separately connected cold source；There are three outlet ends for compressor tool；Pressure
The input end of the first exit end connection rotation detonation combustion room of mechanism of qi, the outlet end connection mixing machine of rotation detonation combustion room
First input end；The input end of the second outlet end connection injector of compressor, the of the outlet end connection mixing machine of injector
Two input ends, the first input end of the outlet end connection turbine of mixing machine；The second of the third outlet end connection turbine of compressor
Input end；Three outlet ends of compressor are used to blower outlet air being divided into three parts: first part enters rotation detonation
Combustion chamber participates in combustion process；Second part by injector enter be set to rotation detonation combustion room tail portion mixing machine in come with
Outlet working medium in rotation detonation combustion room is blended, to realize the cooling to outlet working medium；It is cold that Part III enters turbine participation
But process.
Further, cold source is atmospheric environment, and cycle fluid is discharged directly to atmospheric environment after turbine expansion acting, presses
Mechanism of qi sucks air from atmospheric environment.
Further, rotation detonation combustion room is non-lean premixed combustor, is detonated using thermojet detonator, fuel supply
Mode is that the partial air of blower outlet enters combustion chamber in entry of combustion chamber and fuel side blending on one side.
The simple cycle gas turbine engine based on rotation detonation combustion of the invention, including compressor, rotation detonation combustion room,
Thermojet detonator, injector, mixing machine, turbine, load, cold source, it is characterized in that: air is divided into three after compressor compresses
Point, first part's air enters rotation detonation combustion room and participates in combustion process, and working medium enters mixing machine after burning, with second part
Air is blended, and enters turbine after realizing temperature-fall period；Part III air enters turbine and participates in cooling procedure, final all
Working medium is expelled to atmosphere from turbine outlet.
The above-mentioned simple cycle gas turbine engine based on rotation detonation combustion of the 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, overcoming the traditional combustion room entropy based on isobaric combustion by the supercharging performance of rotation detonation combustion room and increasing
Excessive problem increases the acting ability of combustor exit working medium, significantly improves thermal efficiency of cycle of combustion turbine.
In addition, mixing machine utilizes injector, by blower outlet partial air and the work through the pressurization of rotation detonation combustion room
Matter is blended, and is reduced Temperature of Working and is entered turbine.
The simple cycle gas turbine engine based on rotation detonation combustion of the invention, 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.
Simple cycle gas turbine engine based on rotation detonation combustion of the invention improves the principle of thermal efficiency of cycle: tradition letter
Single cycle gas-turbine combustion chamber combustion process is similar to isobaric combustion process, and there are about 5% pitot loss, and in isobaric combustion
Combustion process entropy increases too big under mode, is that gas turbine cycle process medium entropy increases maximum a part, therefore has lost working medium mistake
More 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 is rotated quick-fried
Hong combustion chamber has certain boosting capability, the acting ability of combustor exit working medium is significantly improved, to improve combustion gas
Turbine thermal efficiency of cycle.
The rotation detonation combustion room of prior art combustion instability under high air-fuel ratio can be made but if air-fuel is smaller
It is excessively high at combustor exit temperature.Can turbine first-stage blade bear so high temperature, and can this is by rotation detonation combustion
It burns room and is applied to the major issue in gas turbine.In contrast, the simple cycle combustion of the invention based on rotation detonation combustion
Gas-turbine, will be from the partial air injection of blower outlet by increasing injector and mixing machine in rotation detonation combustion room tail portion
Into in the high-pressure working medium of combustor exit, temperature-fall period is realized, obtain pressure-air ginseng without further increasing pressure texture
With the working medium blending procedure of rotation detonation combustion room outlet, reduces the wasted work of compressor, further improve gas turbine
Thermal efficiency of cycle.
By the detailed description below in conjunction with attached drawing to highly preferred embodiment of the present invention, these and other of the invention is excellent
Point will be apparent from.
Detailed description of the invention
The present invention can be by reference to being better understood, wherein in institute below in association with description given by attached drawing
Have and has used the same or similar appended drawing reference in attached drawing to indicate same or similar component.The attached drawing is together with following
It is described in detail together comprising in the present specification and forming a part of this specification, and is used to that this is further illustrated
The preferred embodiment and explanation the principle of the present invention and advantage of invention.In the accompanying drawings:
Fig. 1 is the circulation signal for schematically showing the simple cycle gas turbine engine of the invention based on rotation detonation combustion
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 attached 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 certain elements may be exaggerated relative to other elements in attached drawing, with
Just the understanding to the embodiment of the present invention is helped to improve.
Specific embodiment
Exemplary embodiment of the invention is described hereinafter in connection with attached drawing.For clarity and conciseness,
All features of actual implementation mode are not described in the description.It should be understood, however, that developing any this actual implementation
Much decisions specific to embodiment must be made during example, to realize the objectives of developer, for example, symbol
Restrictive condition those of related to system and business is closed, and these restrictive conditions may have with the difference of embodiment
Changed.In addition, it will also be appreciated that although development is likely to be extremely complex and time-consuming, to having benefited from the disclosure
For those skilled in the art of content, this development is only routine task.
Here, and also it should be noted is that, in order to avoid having obscured the present invention because of unnecessary details, in the accompanying drawings
Illustrate only with closely related apparatus structure and/or processing step according to the solution of the present invention, and be omitted and the present invention
The little other details of relationship.
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 burning simple cycle gas turbine engine include compressor, rotation detonation combustion room, injector, mixing machine, turbine, load and
Cold source；The arrival end of compressor and the outlet end of turbine are separately connected cold source；There are three outlet ends for compressor tool；The of compressor
The input end of one outlet end connection rotation detonation combustion room, the first import of the outlet end connection mixing machine of rotation detonation combustion room
End；The input end of the second outlet end connection injector of compressor, the second input end of the outlet end connection mixing machine of injector,
First input end of the outlet end connection turbine of mixing machine；Second input end of the third outlet end connection turbine of compressor；Pressure
Three outlet ends of mechanism of qi are used to blower outlet air being divided into three parts: first part enters rotation detonation combustion room and participates in
Combustion process；Second part is entered by injector in the mixing machine for being set to rotation detonation combustion room tail portion to be fired with rotation detonation
It burns room outlet working medium to be blended, to realize the cooling to outlet working medium；Part III enters turbine and participates in cooling procedure.
Fig. 1 gives an exemplary structure of the simple cycle gas turbine engine of the invention based on rotation detonation combustion
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 cold source.The arrival end of compressor and the outlet end of turbine are distinguished
Connect cold source.
There are three outlet ends for compressor tool；The input end of the first exit end connection rotation detonation combustion room of compressor, rotation
Turn the first input end of the outlet end connection mixing machine of detonation combustion room；The import of the second outlet end connection injector of compressor
End, the second input end of the outlet end connection mixing machine of injector, the first input end of the outlet end connection turbine of mixing machine；Pressure
Second input end of the third outlet end connection turbine of mechanism of qi.
Three outlet ends of compressor are used to blower outlet air being divided into three parts: first part enters rotation detonation
Combustion chamber participates in combustion process；Second part by injector enter be set to rotation detonation combustion room tail portion mixing machine in come with
Outlet working medium in rotation detonation combustion room is blended, to realize the cooling to outlet working medium；It is cold that Part III enters turbine participation
But process.
Wherein, cold source is, for example, atmospheric environment, and cycle fluid is discharged directly to atmospheric environment after turbine expansion acting, presses
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,
Fuel supply mode is that the partial air of blower outlet enters combustion chamber in entry of combustion chamber and fuel side blending on one side.
The thermodynamic cycle side of simple cycle gas turbine engine of the invention based on rotation detonation combustion is described below with reference to Fig. 1
Case are as follows: since cycle fluid enters compressor compression process, 1) compressor compression: working medium is compressed through compressor, increasing temperature and pressure；
2) rotate detonation combustion: the working medium and fuel that first part compresses through compressor enter non-premixed rotation detonation combustion room, warp
Chemical heat release is crossed, the high temperature with high acting ability, high-pressure working medium are generated；3) injection type blends: second part is through calming the anger
The working medium of machine compression enters combustor tail mixing machine by injector, is blended with combustor exit high temperature and pressure working medium,
High temperature and pressure working medium is set to be cooled to the range that turbine first-stage blade is born；4) turbine expansion does work: blending through mixing machine
High temperature and pressure 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 cold source 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
It flashes over and burns the intrinsic superiority of mode, increase the entropy increasing for being less than isobaric combustion process (2) in the entropy of rotation detonation combustion process (2 '),
Loss is smaller, therefore thermal efficiency of cycle is higher.
Simple cycle gas turbine engine based on rotation detonation combustion of the 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, is overcome
Traditional combustion room entropy based on isobaric combustion increases excessive problem, increases the acting ability of combustor exit working medium, improves
Thermal efficiency of cycle of combustion turbine.
Although the embodiment according to limited quantity describes the present invention, 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
Language used in this specification primarily to readable and introduction purpose and select, rather than in order to explain or limit
Determine subject of the present invention and selects.Therefore, without departing from the scope and spirit of the appended claims, for this
Many modifications and changes are obvious for the those of ordinary skill of technical field.For the scope of the present invention, to this
Invent done disclosure be it is illustrative and not restrictive, 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, which is characterized 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 cold source；
The outlet end of the arrival end of the compressor and the turbine is separately connected the cold source；
There are three outlet ends for the compressor tool；The first exit end of the compressor connect it is described rotation detonation combustion room into
The outlet end at mouth end, the rotation detonation combustion room connects the first input end of the mixing machine；The second of the compressor goes out
Mouth end connects the input end of the injector, and the outlet end of the injector connects the second input end of the mixing machine, described
The outlet end of mixing machine connects the first input end of the turbine；The third outlet end of the compressor connects the of the turbine
Two input ends；
Three outlet ends of the compressor are used to the blower outlet air being divided into three parts: described in first part enters
It rotates detonation combustion room and participates in combustion process；Second part is entered by injector is set to the rotation detonation combustion room tail portion
It is 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, which is characterized 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 atmosphere
Air is sucked in environment.
3. the simple cycle gas turbine engine according to claim 1 based on rotation detonation combustion, which is characterized in that the rotation
Turning detonation combustion room is non-lean premixed combustor, is detonated using thermojet detonator, and fuel supply mode is that the compressor goes out
The partial air of mouth enters combustion chamber in entry of combustion chamber and fuel side blending on one side.
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| 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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| 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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| 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 |
| US20210140641A1 (en) * | 2019-11-13 | 2021-05-13 | General Electric Company | Method and system for rotating detonation combustion |
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|---|---|---|---|---|
| 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 |
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