CN206409313U - New change cycle combustion turbine and its unit of calming the anger - Google Patents
New change cycle combustion turbine and its unit of calming the anger Download PDFInfo
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- CN206409313U CN206409313U CN201621437376.XU CN201621437376U CN206409313U CN 206409313 U CN206409313 U CN 206409313U CN 201621437376 U CN201621437376 U CN 201621437376U CN 206409313 U CN206409313 U CN 206409313U
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Abstract
A kind of new change cycle combustion turbine, including combustion chamber, turbine and compressor, the combustion chamber includes entry of combustion chamber and combustor exit, the turbine includes turbine entrance and turbine is exported, the turbine entrance is connected with the combustor exit, the compressor is with the turbine drive connection and including compressor inlet and blower outlet, and the compressor inlet is to receive air.Gas turbine also includes injection type double-work medium compressor, the injection type double-work medium compressor to the combustion chamber to the injection injection air using combustion gas to provide gas-air mixing compressed gas, and the gas-air provided mixes compressed gas in the burning Indoor Combustion to start the gas turbine.After the gas turbine reaches default operating point, the injection type double-work medium compressor stops injection air.
Description
Technical field
The utility model is related to a kind of gas turbine, the new change circulation combustion of more particularly to a kind of achievable combustion engine black starting-up
Gas-turbine and its unit of calming the anger.
Background technology
The compressor of current gas turbine mainly has axial-flow compressor, centrifugal-flow compressor, or axle to wander about as a refugee heart group
Box-like compressor.The gas turbine unit of the compressor of these types is equipped with, needs auxiliary power to open when startup optimization
It is dynamic.So combustion engine is accomplished by installing special accessory power system when in use, so results in the numerous and jumbled of unit.
Utility model content
In view of this, the new change circulating gas wheel of existing combustion engine Starting mode is improved the utility model proposes a kind of
Machine.
The utility model also provides a kind of gas turbine blower group of achievable black starting-up.
A kind of new change cycle combustion turbine, including combustion chamber, turbine and compressor, the combustion chamber enters including combustion chamber
Mouth and combustor exit, the turbine includes turbine entrance and turbine is exported, and the turbine entrance connects with the combustor exit
Logical, the compressor is with the turbine drive connection and including compressor inlet and blower outlet, and the compressor inlet is used
To receive air, in addition to injection type double-work medium compressor, the injection type double-work medium compressor is to the injection using combustion gas
Injection air to the combustion chamber to provide gas-air mixing compressed gas, and the gas-air mixing compressed gas provided exists
The burning Indoor Combustion is to start the gas turbine, after the gas turbine reaches default operating point, the injection type
Double-work medium compressor stops injection air.
In one embodiment, the injection type double-work medium compressor includes mixing chamber and connected at least with the mixing chamber
One-level Atmospheric Absorption room and diffusion room, the Atmospheric Absorption room include setting at the ejecting port to injection air, the ejecting port
A gas nozzle is put, the diffusion room includes mixed gas outlet, and the entry of combustion chamber is connected with the mixed gas outlet.
In one embodiment, the blower outlet is communicated to the mixing chamber.
In one embodiment, the blower outlet and the combustion chamber.
In one embodiment, the Atmospheric Absorption room is closable, when the gas turbine reaches the default work
During point, the injection type double-work medium compressor is by closing the Atmospheric Absorption room to stop injection air.
In one embodiment, the default operating point is the self-sustaining condition of the gas turbine.
A kind of unit of calming the anger of gas turbine, the unit of calming the anger includes：Injection type double-work medium compressor, the injection type
Double-work medium compressor is mixed to the injection injection air using combustion gas with providing gas-air to the combustion chamber of the gas turbine
Compressed gas is closed, the gas-air provided mixes compressed gas in the burning Indoor Combustion to start the gas turbine；
Second compressor, the turbine drive connection of second compressor and the gas turbine so that second compressor is in institute
The driving compressed air of turbine is stated to provide the compressed air required for the gas turbine operation.
In one embodiment, second compressor is axial-flow compressor or centrifugal-flow compressor, and described second calms the anger
The compressed gas of machine is passed through the combustion chamber of the gas turbine, or a compressed gas part for second compressor is passed through institute
Injection type double-work medium compressor is stated, another part is passed through the combustion chamber of the gas turbine.
In one embodiment, the unit of calming the anger works as follows：After the gas turbine reaches self-sustaining condition,
Compressed air required for the gas turbine operation is all provided by second compressor.
In summary, the utility model proposes a kind of new change cycle combustion turbine.The gas turbine is provided with dual-air compressor
Group, the first compressor is injection type double-work medium compressor, and the second compressor is axial-flow type or centrifugal type air compressor.During start
Injection type double-work medium compressor first works, and is passed through combustion gas and injection air, and the laggard combustion chamber of mixing compression promotes gas turbine, then
Drive compressor compressed air.When gas turbine reaches default operating point, for example, reach after self-sustain speed, injection type double-work medium pressure
Contracting power traction emitter is closed, and combustion engine is normally run.The mechanical energy of combustion gas is used the utility model carrys out injection air, realizes combustion
Machine black starting-up, without external auxiliary dynamical system, reduces unit equipment, reduces Maintenance and Repair.And injection type double-work medium compresses
The mixing chamber of machine can help combustion gas and air first to mix and be passed through combustion chambers burn again, and thermo parameters method evenly, is carried in combustion chamber
High burning quality, reduces pollutant emission.
Brief description of the drawings
Fig. 1 is the operational process schematic diagram of the embodiment of the utility model gas turbine one.
Fig. 2 is the operational process schematic diagram of another embodiment of the utility model gas turbine.
Fig. 3 is the structural representation of the injection type double-work medium compressor of gas turbine in Fig. 1.
Fig. 4 shows for the structure that the injection type double-work medium compressor of the utility model gas turbine has two-stage air absorption chamber
It is intended to.
Embodiment
Before describing the embodiments in more detail, it should be understood that the utility model is not limited in the application hereafter or accompanying drawing
Described in detailed construction or arrangement of elements.The embodiment that the utility model can be realized for other manner.Moreover, it should manage
Solution, wording used herein and term are solely for describing purposes, should not the explanation of being construed as limiting property." bag used herein
Include ", "comprising", the similar wording such as " having " meant comprising items listed thereafter, its equivalent and other additional things.It is special
It is not that, when describing " certain element ", the utility model does not limit the quantity of the element as one, can also include many
It is individual.
As depicted in figs. 1 and 2, the utility model provides a kind of new change cycle combustion turbine, including injection type double-work medium
Compressor 10, combustion chamber 12, turbine 14 and compressor 16.Wherein, injection type double-work medium compressor 10 and compressor 16 are common
Composition one is calmed the anger unit.Combustion chamber 12 is connected with injection type double-work medium compressor 10 and turbine 14 respectively, compressor 16 simultaneously with
Injection type double-work medium compressor 10 and combustion chamber 12 are connected (such as Fig. 1), or compressor 16 is connected (such as Fig. 2) with combustion chamber 12.
Turbine 14 and compressor 16 pass through the drive connection of rotating shaft 18.
Injection type double-work medium compressor 10 to formed using the injection injection air of combustion gas combustion gas, air mixing pressure
Contracting gas, so as to start the gas turbine.Specifically, such as Fig. 3, injection type double-work medium compressor 10 include mixing chamber 20 and
The Atmospheric Absorption room 22 and diffusion room 24 connected with mixing chamber 20.In an illustrated embodiment, mixing chamber 20 is hollow tubular, greatly
Aspiration room 22 and diffusion room 24 are separately positioned on the two ends of mixing chamber 20.In other embodiments, Atmospheric Absorption room 22 and expansion
Pressure chamber 24 can also be arranged on other relative positions of mixing chamber 20.
Atmospheric Absorption room 22 includes the ejecting port 26 to injection air, and ejecting port 26 is along gas flow direction in tapered.
A nozzle 28 is provided with ejecting port 26, nozzle 28 is connected to receive combustion gas, such as natural gas with gas pipeline, combustion gas is from nozzle 28
Negative pressure can be formed during ejection, to be mixed in the injection air of ejecting port 26 into mixing chamber with combustion gas.Diffusion room 24 is along air-flow
Flow direction is in flaring, to compress the mixed gas from mixing chamber 20, and diffusion room 24 includes mixed gas outlet 30, to arrange
Go out the mixed gas through overcompression.
It should be appreciated that Atmospheric Absorption room 22 is set to one-level in the present embodiment, in other embodiments, according to air
Injection volume, Atmospheric Absorption room 22 are it can also be provided that multistage.
As shown in figure 4, Atmospheric Absorption room 22 is set to two-stage, for example, mixing chamber is divided into two sections, including first paragraph mixing
Room 23 and second segment mixing chamber 25, the front end of second segment mixing chamber 25 set a secondary injection mouthful 27, and secondary injection mouthful 27 is used to
Injection air, the secondary injection mouthful 27 of the end of first paragraph mixing chamber 23 just to the front end of second segment mixing chamber 25, by first paragraph
Mixed gas in mixing chamber 23 is sprayed into second segment mixing chamber 25.Air injection volume can be increased by secondary injection air, promoted
Enter burning.
In an illustrated embodiment, injection type double-work medium compressor 10 also includes to control ejecting port 26 to open and close
Switch, the switch can be arranged on the master control room of gas turbine, when ejecting port 26 is closed, and it is empty that ejecting port 26 stops injection
Gas.It should be noted that the closing of ejecting port 26 has no effect on nozzle 28 and sprays combustion gas into injection type double-work medium compressor 10.
It should be appreciated that when Atmospheric Absorption room 22 is set to multistage, such as the two-stage in Fig. 4, injection type double-work medium
Compressor 10 has ejecting port 26 and secondary injection mouthful 27.Now being arranged on the switch of master control room can simultaneously or separately control to draw
The opening and closing of loophole 26 and secondary injection mouthful 27.When injection type double-work medium compressor 10 have it is multiple when, switch can be simultaneously
Or independently control the opening and closing of all ejecting ports.
Combustion chamber 12 includes entry of combustion chamber 32 and combustor exit 34, wherein entry of combustion chamber 32 and mixed gas outlet
30 connections, to cause the mixed gas of compression to be burnt into combustion chamber 12.
Turbine 14 includes turbine entrance 36 and turbine outlet 38, and turbine entrance 36 is connected with combustor exit 34 so that combustion
The combustion product (working medium) for burning room enters turbine 14 to drive turbine turbine to rotate, and turbine 14 is rotated then to be driven by rotating shaft 18
The compressed air of compressor 16.Tail gas after acting is emitted or is further processed from turbine outlet 38.
Compressor 16 can be axial-flow type or centrifugal type air compressor, and in the present embodiment, compressor is axial flow type air
Compressor 16.In the embodiment in figure 1, compressor 16 includes compressor inlet 40 and blower outlet 42, compressor inlet 40
To receive air, blower outlet 42 is respectively communicated to mixing chamber 20 and the combustion chamber 12 of injection type double-work medium compressor 10.
The air part that compressor 16 compresses is passed through in the mixing chamber 20 of injection type double-work medium compressor 10, is used for and combustion gas mixing,
Premix can be strengthened, a part is passed through combustion chamber 12 as cooling air and/or auxiliary air.When gas turbine reaches default work
Point when, injection type double-work medium compressor 10 stop injection air, now the compressed air required for gas turbine operation all by
Compressor 16 is provided.
In other embodiments, blower outlet 42 can also be connected only with combustion chamber 12, as shown in Figure 2.Such a situation
Under, after default operating point is reached, injection type double-work medium compressor 10 only provides combustion gas, the pressure that the combustion gas is provided with compressor 16
Contracting air is mixed in combustion chamber 12, now needs to set the combustion connected with injection type double-work medium compressor 10 on combustion chamber 12
Gas jets.Or, after default operating point is reached, combustion gas is provided by other blast tubes, without via injection type double-work medium
Compressor 10 is provided.
The startup method of gas turbine is introduced with reference to the carrying out practically flow of the gas turbine shown in Fig. 1.Combustion gas
When turbine is started shooting, injection type double-work medium compressor 10 first starts, and gas turbine control ejecting port, which is switched, causes ejecting port 26 to open.
Combustion gas sprays into injection type double-work medium compressor 10 through nozzle 28, from the injection air of ejecting port 26, air and combustion gas when combustion gas sprays
Into mixing chamber mixing.Then compressed in diffusion room 24, combustion chambers burn is entered after compression.High temperature refrigerant after burning enters saturating
Flat 14 pairs of turbine turbines acting, work(passes to the compression impellor of compressor 16 by rotating shaft 18, and compression impellor does work to air and pressed
Contracting air simultaneously each leads into the air after compression in the mixing chamber 20 and combustion chamber 12 of injection type double-work medium compressor 10.Wherein
Compressed air, which is passed through in mixing chamber 20, can strengthen premix, be passed through in combustion chamber 12 and can be used as cooling air and/or auxiliary air, make
Must be burnt more stability and high efficiency.The power output of combustion chamber 12 constantly rises, the gas turbine of turbine 14 and calming the anger for compressor 16
The rotating speed of impeller is improved constantly, until reaching default operating point, such as self-sustaining condition.Continue the power output of raising combustion chamber 12
(for example, being passed through more multi fuel), gas turbine control ejecting port switch cause injection type double-work medium compressor 10 one-level or
Multistage Atmospheric Absorption room 22 is slowly closed.The flow that combustion gas is passed through in nozzle 28 can be according to combustion engine Power auto-adjustment.
In summary, the utility model proposes a kind of new change cycle combustion turbine.The gas turbine is provided with dual-air compressor
Group, the first compressor is injection type double-work medium compressor, and the second compressor is axial-flow type or centrifugal type air compressor.During start
Injection type double-work medium compressor first works, and is passed through combustion gas and injection air, and the laggard combustion chamber of mixing compression promotes gas turbine, then
Drive compressor compressed air.When gas turbine reaches default operating point, for example, reach after self-sustain speed, injection type double-work medium pressure
Contracting power traction emitter is closed, and combustion engine is normally run.The mechanical energy of combustion gas is used the utility model carrys out injection air, realizes combustion
Machine black starting-up, without external auxiliary dynamical system, reduces unit equipment, reduces Maintenance and Repair.And injection type double-work medium compresses
The mixing chamber of machine can help combustion gas and air first to mix and be passed through combustion chambers burn again, and thermo parameters method evenly, is carried in combustion chamber
High burning quality, reduces pollutant emission.
Concepts described herein may be embodied to other forms in the case of without departing from its spirit and characteristic.It is disclosed
Specific embodiment should be considered as exemplary rather than restricted.Therefore, scope of the present utility model is by appended right
It is required that, rather than be determined according to these descriptions before.It is any in the letter and equivalency range of claim
Change should all belong to the scope of these claims.
Claims (9)
1. a kind of new change cycle combustion turbine, including combustion chamber, turbine and compressor, the combustion chamber include entry of combustion chamber
And combustor exit, the turbine includes turbine entrance and turbine is exported, and the turbine entrance is connected with the combustor exit,
The compressor is with the turbine drive connection and including compressor inlet and blower outlet, and the compressor inlet is to connect
Receive air, it is characterised in that also include：
Injection type double-work medium compressor, the injection type double-work medium compressor is to the injection injection air using combustion gas with to institute
State combustion chamber and gas-air mixing compressed gas is provided, the gas-air provided mixes compressed gas in the combustion chamber internal combustion
Burn to start the gas turbine, after the gas turbine reaches default operating point, the injection type double-work medium compressor stops
Only injection air.
2. new change cycle combustion turbine as claimed in claim 1, it is characterised in that the injection type double-work medium compressor bag
At least one-level Atmospheric Absorption room and diffusion room for including mixing chamber and being connected with the mixing chamber, the Atmospheric Absorption room include being used to
One gas nozzle is set at the ejecting port of injection air, the ejecting port, and the diffusion room includes mixed gas outlet, the combustion
Chamber inlet is burnt to connect with the mixed gas outlet.
3. new change cycle combustion turbine as claimed in claim 2, it is characterised in that the blower outlet is communicated to described
Mixing chamber.
4. the new change cycle combustion turbine as described in claims 1 to 3 any one, it is characterised in that the compressor goes out
Mouth and the combustion chamber.
5. new change cycle combustion turbine as claimed in claim 2, it is characterised in that the Atmospheric Absorption room is to close
, when the gas turbine reaches the default operating point, the injection type double-work medium compressor is by closing the air
Absorption chamber is to stop injection air.
6. new change cycle combustion turbine as claimed in claim 5, it is characterised in that the default operating point is the combustion gas
The self-sustaining condition of turbine.
7. the unit of calming the anger of a kind of gas turbine, it is characterised in that the unit of calming the anger includes：
Injection type double-work medium compressor, the injection type double-work medium compressor is to the injection injection air using combustion gas with to institute
The combustion chamber for stating gas turbine provides gas-air mixing compressed gas, and the gas-air provided mixes compressed gas described
Burning Indoor Combustion is to start the gas turbine；
Second compressor, the turbine drive connection of second compressor and the gas turbine so that second compressor
In the driving compressed air of the turbine to provide the compressed air required for the gas turbine operation.
8. the unit of calming the anger of gas turbine as claimed in claim 7, it is characterised in that second compressor is axial-flow type pressure
Mechanism of qi or centrifugal-flow compressor, the compressed gas of second compressor are passed through the combustion chamber of the gas turbine, or described
A compressed gas part for second compressor is passed through the injection type double-work medium compressor, and another part is passed through the gas turbine
Combustion chamber.
9. the unit of calming the anger of gas turbine as claimed in claim 7 or 8, it is characterised in that the unit of calming the anger is by such as lower section
Formula works：After the gas turbine reaches self-sustaining condition, the compressed air required for the gas turbine operation is all by institute
The offer of second compressor is provided.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621437376.XU CN206409313U (en) | 2016-12-26 | 2016-12-26 | New change cycle combustion turbine and its unit of calming the anger |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621437376.XU CN206409313U (en) | 2016-12-26 | 2016-12-26 | New change cycle combustion turbine and its unit of calming the anger |
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| Publication Number | Publication Date |
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| CN206409313U true CN206409313U (en) | 2017-08-15 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201621437376.XU Active CN206409313U (en) | 2016-12-26 | 2016-12-26 | New change cycle combustion turbine and its unit of calming the anger |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109374234A (en) * | 2018-12-06 | 2019-02-22 | 中国航发沈阳发动机研究所 | Examine the pilot system and method for becoming circulation compressor adsorption system leakproofness |
-
2016
- 2016-12-26 CN CN201621437376.XU patent/CN206409313U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109374234A (en) * | 2018-12-06 | 2019-02-22 | 中国航发沈阳发动机研究所 | Examine the pilot system and method for becoming circulation compressor adsorption system leakproofness |
| CN109374234B (en) * | 2018-12-06 | 2019-08-23 | 中国航发沈阳发动机研究所 | Examine the pilot system and method for becoming circulation compressor adsorption system leakproofness |
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