CN106499519A - There is the LNG gas turbines of interstage cooling - Google Patents
There is the LNG gas turbines of interstage cooling Download PDFInfo
- Publication number
- CN106499519A CN106499519A CN201611249203.XA CN201611249203A CN106499519A CN 106499519 A CN106499519 A CN 106499519A CN 201611249203 A CN201611249203 A CN 201611249203A CN 106499519 A CN106499519 A CN 106499519A
- Authority
- CN
- China
- Prior art keywords
- lng
- compressor
- heat exchanger
- natural gas
- compressed air
- 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
- 238000001816 cooling Methods 0.000 title claims abstract description 19
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 108
- 230000006835 compression Effects 0.000 claims abstract description 72
- 238000007906 compression Methods 0.000 claims abstract description 72
- 239000003345 natural gas Substances 0.000 claims abstract description 54
- 239000007789 gas Substances 0.000 claims abstract description 40
- 238000002485 combustion reaction Methods 0.000 claims abstract description 25
- 239000000567 combustion gas Substances 0.000 claims abstract description 9
- 230000008016 vaporization Effects 0.000 claims description 20
- 238000009834 vaporization Methods 0.000 claims description 17
- 238000010276 construction Methods 0.000 claims description 6
- 238000011144 upstream manufacturing Methods 0.000 claims description 6
- 238000000034 method Methods 0.000 description 3
- 238000005086 pumping Methods 0.000 description 3
- 239000003344 environmental pollutant Substances 0.000 description 2
- 231100000719 pollutant Toxicity 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000008246 gaseous mixture Substances 0.000 description 1
- 230000000670 limiting effect Effects 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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
- 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
- F02C7/143—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid before or between the compressor stages
-
- 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
- F02C3/22—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 the fuel or oxidant being gaseous at standard temperature and pressure
-
- 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
- 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
- F02C7/22—Fuel supply systems
- F02C7/224—Heating fuel before feeding to the burner
-
- 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
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/213—Heat transfer, e.g. cooling by the provision of a heat exchanger within the cooling circuit
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
A kind of LNG gas turbines with interstage cooling, including combustor, turbine and compressor, the compressor is with the combustion chamber in order to combustor offer compressed air, the turbine and the combustion chamber are in order to receiving the combustion gas working medium of the combustor output, the compressor and the turbine drive connection, the compressor includes prime compression impellor, rear class compression impellor and the compressed air channel being communicated between the prime compression impellor and rear class compression impellor, the gas turbine also includes the natural gas transportation passage for conveying natural gas to the combustor, the compressor also includes First Heat Exchanger, compressed air in the natural gas that the First Heat Exchanger is constructed and is connected in the natural gas transportation passage and the compressed air channel is exchanged heat to reduce the temperature of the compressed air.
Description
Technical field
The present invention relates to gas turbine field, more particularly to a kind of LNG with interstage cooling for improving combustion engine efficiency
Gas turbine.
Background technology
When gas turbine works, compressor impeller compressed air enters combustor and fuel mixed combustion.There is a kind of raising
The method of combustion engine power, is to increase number of compression stages to improve air pressure ratio.Can so have a problem that, air is compressed through leading portion
Shi Wendu improves, now again when back segment further compresses with regard to relative difficulty some.Then with regard between compressor stage plus in cold set
Standby improving the efficiency of compressor.For the combustion engine for burning natural gas, generally exchanged heat by water.Also a kind of raising combustion engine efficiency
Method be to enter compressor before air heat-exchange cooling, and with normal temperature air heat exchange medium must compare air themperature
Much lower ability is efficiently cooled down.The auxiliary equipment of this heat exchange input is more, and heat exchange efficiency is not high, and volume is relatively large.
LNG environment-protecting cleans, price are relatively low.For the combustion engine for burning LNG, the cold energy of LNG contains abundant, and it is one not to be used
Plant and greatly waste.
Content of the invention
In view of this, the present invention proposes a kind of LNG gas turbines with interstage cooling for making full use of LNG cold energy.
The present invention proposes a kind of LNG gas turbines with interstage cooling, including combustor, turbine and compressor, described
Compressor with the combustion chamber in order to provide compressed air to the combustor, used with the combustion chamber by the turbine
To receive the combustion gas working medium of the combustor output, the compressor and the turbine drive connection, before the compressor includes
Level compression impellor, rear class compression impellor and the compressed air being communicated between the prime compression impellor and rear class compression impellor
Passage, the gas turbine also include that the natural gas transportation passage for conveying natural gas to the combustor, the compressor are also wrapped
First Heat Exchanger is included, the First Heat Exchanger is constructed and is connected to the LNG in the natural gas transportation passage and the pressure
The temperature exchanged heat to reduce the compressed air by compressed air in contracting air duct is while at least part of LNG vapour
Change.
In one embodiment, the compressor includes air input passage and the second heat exchanger, the air input passage
Connect with the prime compression impellor with to the prime compression impellor input environment air, second heat exchanger construction and company
It is connected into so that the LNG in the natural gas transportation passage is exchanged heat to reduce with the input air in the air input passage
The temperature of the input air at least part of LNG vaporization simultaneously, in the flow direction of the natural gas transportation passage, described the
Two heat exchangers are located at the First Heat Exchanger upstream.
In one embodiment, the natural gas transportation passage end connects LNG delivery pumps, and the other end is communicated to the combustion
Burn room, the LNG delivery pumps are in order to pumping the LNG to the natural gas transportation passage.
The present invention also proposes a kind of LNG gas turbines with interstage cooling, including combustor, turbine and compressor, institute
Compressor is stated with the combustion chamber in order to combustor offer compressed air, the turbine and the combustion chamber
In order to receive the combustion gas working medium of the combustor output, the compressor is included with the turbine drive connection, the compressor
Some grades of compression units, are communicated with compressed air channel between the compression unit per two-stage neighboring, and the gas turbine also includes
To the natural gas transportation passage that the combustor conveys natural gas, the compressor also includes some First Heat Exchangers, wherein every
One First Heat Exchanger is corresponding with a wherein compressed air channel, and at least one of which First Heat Exchanger is constructed and is connected to institute
State the LNG in natural gas transportation passage exchanged heat with the compressed air in the corresponding compressed air channel described to reduce
The temperature of the compressed air at least part of LNG vaporization simultaneously.
In one embodiment, the compressor includes air input passage and the second heat exchanger, the air input passage
Connect with the first order compression unit of some grades of compression units with to the first order compression unit input environment air, institute
State defeated in the second heat exchanger construction and the LNG that is connected in the natural gas transportation passage and the air input passage
Enter air to be exchanged heat to reduce the temperature of the input air while at least part of LNG vaporization, defeated in the natural gas
Send in the flow direction of passage, second heat exchanger is located at the upstream of any one First Heat Exchanger.
In one embodiment, the natural gas transportation passage end connects LNG delivery pumps, and the other end is communicated to the combustion
Burn room, the LNG delivery pumps are in order to pumping the LNG to the natural gas transportation passage.
In sum, the present invention provides a kind of LNG gas turbines with interstage cooling.The LNG gas turbines are calmed the anger
Machine includes some grades of compression units, is communicated with compressed air channel, each compressed air between the compression unit per two-stage neighboring
One First Heat Exchanger is set on passage so that the LNG in natural gas transportation passage is changed with the compressed air in compressed air channel
Heat is reducing the temperature of compressed air.Additionally, the present invention is also set in the air input passage connected with first order compression unit
Put the second heat exchanger so that LNG and input air are exchanged heat to reduce the temperature of input air.The LNG combustion gas wheels of the present invention
Machine absorbs the heat energy of compressed air between the input air of compressor and level vaporizing LNG using LNG as low-temperature receiver.Take full advantage of
The energy that LNG contains in itself, reduces the volume of heat transmission equipment, improves heat exchange efficiency, increases capacity usage ratio, with a kind of more preferable
Mode improves the efficiency of gas turbine, reduces pollutant emission, saves use cost.
Description of the drawings
Fig. 1 is the simplified structural representation of the LNG gas turbines of the present invention.
Specific embodiment
Before describing the embodiments in more detail, it should be understood that the invention is not restricted in the application institute hereafter or in accompanying drawing
The detailed construction or arrangement of elements of description.The present invention can be the embodiment that alternate manner is realized.Furthermore, it is to be understood that this paper institutes
The wording and term for using is solely for describing purposes, should not the explanation of being construed as limiting property." including " used herein, "comprising",
The similar wording such as " with " is meant comprising items listed thereafter, its equivalent and other additional things.Particularly, work as description
When " certain element ", the present invention does not limit the quantity of the element as one, it is also possible to including multiple.
The present invention provides a kind of LNG gas turbines with interstage cooling, and the LNG gas turbines include combustor, turbine
And compressor., in order to provide compressed air to combustor, turbine and combustion chamber are in order to receiving for compressor and combustion chamber
The combustion gas working medium of combustor output, compressor and turbine drive connection.LNG gas turbines also include conveying natural gas to combustor
Natural gas transportation passage, the natural gas transportation passage end connects LNG delivery pumps, and LNG delivery pumps are natural in order to pass through
Gas transfer passage pumps LNG to combustor, and the other end is communicated to combustor.
Compressor includes some grades of compression units, air input passage, some First Heat Exchangers and one second heat exchanger.Its
Middle air input passage connects to be input into first order compression unit with the first order compression unit of some grades of compression units
Defeated in surrounding air, the second heat exchanger construction and the LNG that is connected in natural gas transportation passage and air input passage
Enter air to be exchanged heat, to reduce the temperature of input air, while at least partly LNG vaporization.So, by the second heat exchanger
Natural gas is actually the gaseous mixture of LNG/ gaseous natural gas.It is communicated with compressed air to lead between compression unit per two-stage neighboring
Road, each First Heat Exchanger are corresponding with a wherein compressed air channel, and each First Heat Exchanger is constructed and is connected to day
So the LNG in gas transfer passage is exchanged heat with the compressed air in corresponding compressed air channel, to reduce compressed air
Temperature.
Specifically, some First Heat Exchangers and the second heat exchanger are respectively positioned on natural gas transportation passage, the second heat exchanger
It is also located in air input passage, to realize the heat exchange of LNG and input air, makes at least part of LNG vaporization, reduce input air
Temperature；Some First Heat Exchangers are located on corresponding compressed air channel respectively, to realize changing for compressed air between LNG and level
Heat, the temperature of compressed air between reduction stages, and make at least part of LNG vaporization.In the flow direction of natural gas transportation passage, second changes
Hot device is located at the upstream of any one First Heat Exchanger.
It is specifically described so that compressor has two stages of compression unit as an example below.As shown in Figure 1, there is provided one has between level
The LNG gas turbines 10 of cooling, the LNG gas turbines 10 include combustor 12, turbine 14, compressor 16 and defeated to combustor 12
Send the natural gas transportation passage 18 of natural gas.Combustor 12 includes that entry of combustion chamber 20 and combustor exit 22, turbine 14 include
Turbine entrance 24 and turbine outlet 26.Turbine entrance 24 connects to receive combustion gas working medium with combustor exit 22, compressor 16 with
Entry of combustion chamber 20 connects to provide compressed air to combustor 12.One end of natural gas transportation passage 18 and LNG delivery pumps
28 connections, the other end are communicated to combustor 12, and LNG delivery pumps 28 are in order to the pumping LNG of natural gas transportation passage 18, LNG vaporization
Backward combustor 12 is conveyed.
In an illustrated embodiment, compressor 16 includes that two stages of compression unit, the two stages of compression unit include prime pressure
Gas impeller 30 and rear class compression impellor 32, are communicated with compressed air channel between prime compression impellor 30 and rear class compression impellor 32
34.Prime compression impellor 32 includes prime compression impellor entrance 36 and prime compression impellor outlet 38, and rear class compression impellor 32 is wrapped
Rear class compression impellor entrance 40 and rear class compression impellor outlet 42 is included, rear class compression impellor outlet 42 is connected with combustor 12.Before
Compressed air channel 34 is formed between level compression impellor outlet 38 and rear class compression impellor entrance 40.
Compressor 16 also includes air input passage 44, First Heat Exchanger 46 and the second heat exchanger 48.Air input passage
44 are connected with prime compression impellor entrance 36 so as to 30 input environment air of prime compression impellor, the second heat exchanger 48 is constructed and connected
It is connected into so that the LNG in natural gas transportation passage 18 is exchanged heat with the input air in air input passage 44, defeated to reduce
Enter the temperature of air, while causing LNG vaporization.First Heat Exchanger 46 is constructed and is connected in natural gas transportation passage 18
LNG is exchanged heat with the compressed air in compressed air channel 34, to reduce the temperature of compressed air, while further such that
LNG vaporization.
In an illustrated embodiment, First Heat Exchanger 46 and the second heat exchanger 48 are located on natural gas transportation passage 18.Its
In, the second heat exchanger 48 is also located in air input passage 44, to realize the heat exchange of LNG and input air；First Heat Exchanger 46
It is also located on compressed air channel 34, to realize the heat exchange of compressed air between LNG and level.Flow direction in natural gas transportation passage 18
On, the second heat exchanger 48 is located at the upstream of First Heat Exchanger 46.
Below the operational process of the LNG gas turbines of the present invention is briefly described.
During start, LNG delivery pumps 28 first run, and conveying LNG enters the second heat exchanger 48, enters prime compression impellor 30
Air first passes through the second heat exchanger 48, and the LNG in the second heat exchanger 48 is cooled down to input air, while LNG also can
Carry out a certain degree of vaporization.The gaseous natural gas for vaporizing incomplete LNG and/or low temperature continue to flow into First Heat Exchanger
46.LNG/ gaseous natural gas of the air in First Heat Exchanger 46, First Heat Exchanger 46 compressed through prime compression impellor 30
Above-mentioned compressed air is cooled down, the compressed air after cooling is passed through rear class compression impellor 32 and continues compression, after heat absorption
The gaseous natural gas of vaporization are passed through combustor 14, and the air after compressing through rear class compression impellor 32 is passed through combustor 14.After vaporization
The mixed combustion in combustor 14 of gaseous natural gas and compressed air, promote turbine 16 turbine acting.
Above-described embodiment is illustrated for two stages of compression unit, i.e. prime compression impellor and rear class compression impellor.Should
When being understood by, for prime compression impellor and rear class compression impellor are just for any two successive stages compression impellor.For many
Remaining two stages of compression unit, the such as situation of 3 grades of compression units, first order impeller and second level impeller constitute two successive stages, then and the
One stage impeller is referred to as prime, and second level impeller is referred to as rear class.Second level impeller and third level impeller also constitute two successive stages,
Now second level impeller is referred to as prime, and third level impeller is referred to as rear class.
It should be appreciated that in the above-described embodiments, compressor includes the two-stage of same compressor or the pressure more than two-stage
Gas impeller.In other embodiments, each compression unit of compressor can also implement into single compressor, now each compressor
Can be coaxially connected with turbine.When the compression unit of compressor is single compressor, its structure setting mode is calmed the anger with above-mentioned
The structure setting mode of impeller is similar to, and differs only in and for compression impellor to be substituted for compressor.
In sum, the present invention provides a kind of LNG gas turbines with interstage cooling.The LNG gas turbines are calmed the anger
Machine includes some grades of compression units, is communicated with compressed air channel, each compressed air between the compression unit per two-stage neighboring
One First Heat Exchanger is set on passage so that the LNG in natural gas transportation passage is changed with the compressed air in compressed air channel
Heat is to reduce the temperature of compressed air, while at least partly LNG vaporization.Additionally, the present invention is also being connected with first order compression unit
Second heat exchanger is set in logical air input passage so that LNG and input air are exchanged heat to reduce the temperature of input air
Degree.The LNG gas turbines of the present invention absorb the heat energy of compressed air between the input air of compressor and level using LNG as low-temperature receiver,
The heat energy for reclaiming air is used for vaporizing LNG, while reducing air themperature.The energy that LNG contains in itself is taken full advantage of, reduction is changed
The volume of hot equipment, improves heat exchange efficiency, increases capacity usage ratio, with the effect that a kind of better way improves gas turbine
Rate, reduces pollutant emission, saves use cost.
Concepts described herein may be embodied to other forms in the case of without departing from its spirit and characteristic.Disclosed
Specific embodiment should be considered exemplary rather than restricted.Therefore, the scope of the present invention be by appended claim,
Rather than be determined according to these descriptions before.Any change in the letter of claim and equivalency range is all
The scope of these claim should be belonged to.
Claims (6)
1. a kind of LNG gas turbines with interstage cooling, including combustor, turbine and compressor, the compressor with described
, in order to provide compressed air to the combustor, the turbine and the combustion chamber are in order to receiving the combustion for combustion chamber
Burn the combustion gas working medium of room output, the compressor and the turbine drive connection, the compressor include prime compression impellor, after
Level compression impellor and the compressed air channel being communicated between the prime compression impellor and rear class compression impellor, the combustion gas
Turbine also includes the natural gas transportation passage for conveying natural gas to the combustor, it is characterised in that the compressor also includes
First Heat Exchanger, the First Heat Exchanger are constructed and are connected to the LNG in the natural gas transportation passage and the compression
The temperature exchanged heat to reduce the compressed air by compressed air in air duct is while at least part of LNG vaporization.
2. there is the LNG gas turbines of interstage cooling as claimed in claim 1, it is characterised in that the compressor includes sky
Gas input channel and the second heat exchanger, the air input passage connect to calm the anger to the prime with the prime compression impellor
Impeller input environment air, second heat exchanger construction and the LNG being connected in the natural gas transportation passage and institute
Temperature that the input air in air input passage exchanged heat to reduce the input air is stated while at least part of LNG
Vaporization, in the flow direction of the natural gas transportation passage, second heat exchanger is located at the First Heat Exchanger upstream.
3. there is the LNG gas turbines of interstage cooling as claimed in claim 1, it is characterised in that the natural gas transportation is led to
Road one end connects LNG delivery pumps, and the other end is communicated to the combustor, and the LNG delivery pumps are in order to defeated to the natural gas
Send passage input LNG.
4. a kind of LNG gas turbines with interstage cooling, including combustor, turbine and compressor, the compressor with described
, in order to provide compressed air to the combustor, the turbine and the combustion chamber are in order to receiving the combustion for combustion chamber
The combustion gas working medium of room output, the compressor and the turbine drive connection is burnt, the compressor includes some grades of compression units,
Compressed air channel is communicated between compression unit per two-stage neighboring, the gas turbine also includes conveying to the combustor
The natural gas transportation passage of natural gas, it is characterised in that the compressor also includes some First Heat Exchangers, each of which first
Heat exchanger is corresponding with a wherein compressed air channel, and at least one of which First Heat Exchanger is constructed and is connected to described natural
LNG in gas transfer passage is exchanged heat empty to reduce the compression with the compressed air in the corresponding compressed air channel
The temperature of the gas at least part of LNG vaporization simultaneously.
5. there is the LNG gas turbines of interstage cooling as claimed in claim 4, it is characterised in that the compressor includes sky
Gas input channel and the second heat exchanger, the air input passage are connected with the first order compression unit of some grades of compression units
Pass to the first order compression unit input environment air, second heat exchanger construction and be connected to the natural gas
Input air in LNG in transfer passage and the air input passage is exchanged heat to reduce the temperature of the input air
The simultaneously at least part of LNG vaporization, in the flow direction of the natural gas transportation passage, second heat exchanger is located at any one
The upstream of the individual First Heat Exchanger.
6. there is the LNG gas turbines of interstage cooling as claimed in claim 4, it is characterised in that the natural gas transportation is led to
Road one end connects LNG delivery pumps, and the other end is communicated to the combustor, and the LNG delivery pumps are in order to defeated to the natural gas
Passage is sent to pump the LNG.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611249203.XA CN106499519A (en) | 2016-12-29 | 2016-12-29 | There is the LNG gas turbines of interstage cooling |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611249203.XA CN106499519A (en) | 2016-12-29 | 2016-12-29 | There is the LNG gas turbines of interstage cooling |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106499519A true CN106499519A (en) | 2017-03-15 |
Family
ID=58334700
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611249203.XA Pending CN106499519A (en) | 2016-12-29 | 2016-12-29 | There is the LNG gas turbines of interstage cooling |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106499519A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018119921A1 (en) * | 2016-12-29 | 2018-07-05 | 深圳智慧能源技术有限公司 | Lng gas turbine with inter-stage cooling |
| CN109026400A (en) * | 2018-08-01 | 2018-12-18 | 中国华能集团有限公司 | A kind of gas turbine engine systems and method using the pre-heating fuel that exchanges heat between grade |
| CN110953069A (en) * | 2019-12-17 | 2020-04-03 | 中国能源建设集团广东省电力设计研究院有限公司 | Multi-energy coupling power generation system of gas turbine power station |
| CN114876641A (en) * | 2022-06-14 | 2022-08-09 | 西安热工研究院有限公司 | Gas turbine inlet air cooling system utilizing LNG gasification cold energy and working method thereof |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060174627A1 (en) * | 2005-02-04 | 2006-08-10 | Siemens Westinghouse Power Corp. | Gas turbine cycle |
| US20140000275A1 (en) * | 2012-06-29 | 2014-01-02 | Icr Turbine Engine Corporation | Lng fuel handling for a gas turbine engine |
| CN105863752A (en) * | 2016-06-01 | 2016-08-17 | 中国科学院工程热物理研究所 | Compressed air energy storage system and method utilizing cold energy of liquefied natural gas |
| CN206319962U (en) * | 2016-12-29 | 2017-07-11 | 深圳智慧能源技术有限公司 | LNG gas turbines with cascade EDFA |
-
2016
- 2016-12-29 CN CN201611249203.XA patent/CN106499519A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060174627A1 (en) * | 2005-02-04 | 2006-08-10 | Siemens Westinghouse Power Corp. | Gas turbine cycle |
| US20140000275A1 (en) * | 2012-06-29 | 2014-01-02 | Icr Turbine Engine Corporation | Lng fuel handling for a gas turbine engine |
| CN105863752A (en) * | 2016-06-01 | 2016-08-17 | 中国科学院工程热物理研究所 | Compressed air energy storage system and method utilizing cold energy of liquefied natural gas |
| CN206319962U (en) * | 2016-12-29 | 2017-07-11 | 深圳智慧能源技术有限公司 | LNG gas turbines with cascade EDFA |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018119921A1 (en) * | 2016-12-29 | 2018-07-05 | 深圳智慧能源技术有限公司 | Lng gas turbine with inter-stage cooling |
| CN109026400A (en) * | 2018-08-01 | 2018-12-18 | 中国华能集团有限公司 | A kind of gas turbine engine systems and method using the pre-heating fuel that exchanges heat between grade |
| CN110953069A (en) * | 2019-12-17 | 2020-04-03 | 中国能源建设集团广东省电力设计研究院有限公司 | Multi-energy coupling power generation system of gas turbine power station |
| CN114876641A (en) * | 2022-06-14 | 2022-08-09 | 西安热工研究院有限公司 | Gas turbine inlet air cooling system utilizing LNG gasification cold energy and working method thereof |
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