CN102900531A - Combustion gas turbine system with inlet cooling and indirect cooling - Google Patents
Combustion gas turbine system with inlet cooling and indirect cooling Download PDFInfo
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- CN102900531A CN102900531A CN2012104056740A CN201210405674A CN102900531A CN 102900531 A CN102900531 A CN 102900531A CN 2012104056740 A CN2012104056740 A CN 2012104056740A CN 201210405674 A CN201210405674 A CN 201210405674A CN 102900531 A CN102900531 A CN 102900531A
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02A—TECHNOLOGIES FOR ADAPTATION TO CLIMATE CHANGE
- Y02A30/00—Adapting or protecting infrastructure or their operation
- Y02A30/27—Relating to heating, ventilation or air conditioning [HVAC] technologies
- Y02A30/274—Relating to heating, ventilation or air conditioning [HVAC] technologies using waste energy, e.g. from internal combustion engine
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Abstract
The invention relates to a combustion gas turbine system with inlet cooling and indirect cooling, which comprises a low-pressure compressor, a high-pressure compressor, a combustor and a turbine, and is characterized in that: a gas turbine inlet cooler is arranged at the front end of the low-pressure compressor; an indirect cooler is arranged at the rear end of the low-pressure compressor; a cooling medium outlet of an absorbing type refrigerator is respectively connected with cooling medium inlets of the gas turbine inlet cooler and the indirect cooler; and a cooling medium backflow port of the absorbing type refrigerator is respectively connected with cooling medium outlets of the gas turbine inlet cooler and the indirect cooler. The combustion gas turbine system utilizes the cold energy generated by the absorbing type refrigerator to cool the air at a gas turbine inlet and the air compressed by the low-pressure compressor; compared with an electric refrigerating technology, the combustion gas turbine system has the advantages that no extra energy consumption exists and the whole economical efficiency is increased; compared with the traditional inlet water-spraying cooling and indirect cooling technology, the combustion gas turbine system has the advantages that the large amount of cooling water is not required when the closed type circulating is adopted, the smoke waste heat is effectively utilized while the extra system energy consumption and resource consumption are not increased; and the running efficiency and power of the combustion gas turbine for a power system are effectively increased.
Description
Technical field
The present invention relates to a kind of gas turbine, particularly relate to a kind of tape entry cooling and a cold gas turbine engine systems.
Background technique
Refrigeration technique between gas turbine is because the consideration of economic serviceability, is mainly used in ship power and has on the regional generation project of a large amount of water source areas, and generally do open cycle.A large amount of consumption of cooling medium and to the objective demand in place, refrigeration technique is at the broad development in gas turbine field between having limited; So that this achievement is being fired the practical application of mechanomotive force aspect is less always.
Simultaneously, the thermodynamic cycle of gas turbine all is open cycle, and the high-temperature flue gas that produces after the turbine expansion acting directly enters in the atmosphere.Its high-temperature gas is larger to the contaminativity of environment on the one hand, and simultaneously, its a large amount of heat is also wasted along with discharging.Utilize in the industry at present the combined-cycle technology of fume afterheat comparatively ripe, but it need to increase outside a large amount of initial costs, the area requirements in place is also greatly improved.And this considers its cost and operational efficiency for load is not very large distributing-supplying-energy system, and its Economy also has the space of further raising.
All refrigeration technology be to take in order raising the efficiency to existing gas turbine inlet air, electricity refrigeration and entrance water spray refrigeration mainly to be divided into.For intake air electricity refrigeration, the electric weight of its consumption is extra energy consumption, has reduced the Economy of gas turbine engine systems integral body; Although entrance water spray refrigeration has relative advantage in energy consumption, it has consumed a large amount of cooling waters.And for cold, it also needs the cooling medium that provides a large amount of.
Summary of the invention
In order effectively to utilize fume afterheat, improve Gas Turbine Output and improve compressor efficiency, the invention provides a kind of tape entry cooling and a cold gas turbine engine systems, utilize the energy of fume afterheat to drive Absorption Refrigerator, air behind cooling combustion machine intake air and the low pressure compressor, thus heighten the operational efficiency of gas turbine and exert oneself.
The technical solution used in the present invention is: a kind of tape entry cooling and a cold gas turbine engine systems comprise low pressure compressor, high-pressure compressor, firing chamber, turbine; It is characterized in that the low pressure compressor front end is provided with combustion machine entrance cooler, the air outlet slit of combustion machine entrance cooler is connected with the low pressure compressor air inlet; The low pressure compressor rear end is provided with inter cooler, and the low pressure compressor air outlet slit is connected with the inter cooler air inlet, and the inter cooler air outlet slit is connected with the air inlet of high-pressure compressor; The air outlet slit of high-pressure compressor is connected with the air inlet of firing chamber, and the air outlet slit of firing chamber is connected with the smoke inlet of turbine, and turbine is connected with generator by coupling; The smoke outlet of turbine is connected with the smoke inlet of Absorption Refrigerator, the outlet of the cooling medium of Absorption Refrigerator is connected the cooling medium entrance with combustion machine entrance cooler respectively and is connected with inter cooler, the cooling medium refluxing opening of Absorption Refrigerator is connected cooling medium with combustion machine entrance cooler respectively and is exported and be connected with inter cooler; Low pressure compressor, high-pressure compressor are coaxial the connection with turbine.
Described Absorption Refrigerator is provided with cooling medium outlet that cooling medium entrance and combustion machine entrance cooler and inter cooler be provided with and is open, and cooling medium is done open cycle.
Described Absorption Refrigerator is provided with the cooling medium entrance and links to each other respectively with the cooling medium outlet that inter cooler is provided with combustion machine entrance cooler, and cooling medium is closed cycle.
The cold that the present invention utilizes Absorption Refrigerator to produce cools off pressurized air behind combustion machine intake air and the low pressure compressor, comparing with electric refrigeration technology does not have extra energy consumption to improve whole Economy, compare with a refrigeration technique with traditional entrance water spray refrigeration when adopting closed cycle and do not need a large amount of cooling waters, effectively utilize fume afterheat on the one hand, do not increased its extra system energy consumption and resource consumption; On the other hand Effective Raise gas turbine be main power system operational efficiency and exert oneself.
Description of drawings
Fig. 1 is closed cycle structural representation of the present invention;
Fig. 2 is open cycle structural representation of the present invention.
Number in the figure title: 1 combustion machine entrance cooler; 2 low pressure compressors; 3 inter coolers; 4 high-pressure compressors; 5 firing chambers; 6 turbines; 7 generators; 8 Absorption Refrigerators; 9 pass through coupling.
A combustion machine entrance cooler air entrance; B firing chamber fuel inlet; C Absorption Refrigerator smoke outlet; D, E Absorption Refrigerator cooling medium entrance; F, the outlet of G Absorption Refrigerator cooling medium.
Embodiment
The embodiment of the invention one is illustrated in figure 1 as the closed cycle structure, and this tape entry cooling and a cold gas turbine engine systems comprise low pressure compressor 2, high-pressure compressor 4, firing chamber 5, turbine 6; Low pressure compressor 2 front ends are provided with combustion machine entrance cooler 1, and the air outlet slit of combustion machine entrance cooler 1 is connected with low pressure compressor 2 air inlets; Low pressure compressor 2 rear ends are provided with inter cooler 3, and low pressure compressor 2 air outlet slits are connected with inter cooler 3 air inlets, and inter cooler 3 air outlet slits are connected with the air inlet of high-pressure compressor 4; The air outlet slit of high-pressure compressor 4 is connected with the air inlet of firing chamber 5, and the air outlet slit of firing chamber is connected with the smoke inlet of turbine 6, and turbine 6 is connected with generator 7 by coupling 9; The smoke outlet of turbine 6 is connected with the smoke inlet of Absorption Refrigerator 8, and cooling medium outlet F, the G of Absorption Refrigerator 8 is connected with the cooling medium entrance that combustion machine entrance cooler 1 is connected with inter cooler respectively; Absorption Refrigerator 8 is provided with cooling medium entrance D, E and links to each other respectively with the cooling medium outlet that combustion machine entrance cooler 1 and inter cooler 3 are provided with, and cooling medium is closed cycle; Low pressure compressor 2, high-pressure compressor 4 are coaxial the connection with turbine 6.
When gas turbine operation, the fume afterheat of gas turbine produces cold by Absorption Refrigerator 8.After air enters combustion machine entrance cooler 1 by combustion machine entrance cooler air entrance A, enter low pressure compressor 2 after being absorbed the cooling medium cooling that formula refrigerator 8 produces, the air of low pressure compressor 2 enters after compression and enters high-pressure compressor 4 after inter cooler 3 is absorbed the cooling medium cooling that formula refrigerator 8 produces, the air of high-pressure compressor compression enters firing chamber 5 and carries out the blending burning with the fuel that firing chamber fuel inlet B enters, high-temperature flue gas enters turbine 6 expansion actings, drives low pressure compressor 2, high-pressure compressor 4 and generator 7.The waste heat flue gas that has done work enters Absorption Refrigerator 8 and freezes as its energy source, and flue gas is discharged by Absorption Refrigerator smoke outlet C after the refrigeration.The cooling medium closed cycle of Absorption Refrigerator 8 does not need a large amount of cooling waters, has effectively utilized fume afterheat on the one hand, does not increase its extra system energy consumption and resource consumption; On the other hand Effective Raise gas turbine be main power system operational efficiency and exert oneself.
The embodiment of the invention two is illustrated in figure 2 as the open cycle structure, be that with embodiment's difference the cooling medium entrance on the Absorption Refrigerator 8 is open with the cooling medium outlet that combustion machine entrance cooler 1 and inter cooler 3 are provided with, cooling medium is done open cycle, applicable water source is abundant and utilize easily environment, takes to enter local water source after local water source enters combustion machine entrance cooler 1 and inter cooler 3 after through the Absorption Refrigerator cooling.
Claims (3)
1. a tape entry cools off and a cold gas turbine engine systems, comprises low pressure compressor (2), high-pressure compressor (4), firing chamber (5), turbine (6); It is characterized in that low pressure compressor (2) front end is provided with combustion machine entrance cooler (1), the air outlet slit of combustion machine entrance cooler (1) is connected with low pressure compressor (2) air inlet; Low pressure compressor (2) rear end is provided with inter cooler (3), and low pressure compressor (2) air outlet slit is connected with inter cooler (3) air inlet, and inter cooler (3) air outlet slit is connected with the air inlet of high-pressure compressor (4); The air outlet slit of high-pressure compressor (4) is connected with the air inlet of firing chamber (5), and the air outlet slit of firing chamber is connected with the smoke inlet of turbine (6), and turbine (6) is connected with generator (7) by coupling (9); The smoke outlet of turbine (6) is connected with the smoke inlet of Absorption Refrigerator (8), and the outlet of the cooling medium of Absorption Refrigerator (8) is connected 3 with combustion machine entrance cooler (1) with inter cooler respectively) the cooling medium entrance be connected; Low pressure compressor (2), high-pressure compressor (4) are coaxial the connection with turbine (6).
2. tape entry according to claim 1 cools off and a cold gas turbine engine systems, it is characterized in that described Absorption Refrigerator (8) is provided with cooling medium that cooling medium entrance and combustion machine entrance cooler (1) and inter cooler (3) be provided with and exports and be open, cooling medium is done open cycle.
3. tape entry according to claim 1 cools off and a cold gas turbine engine systems, it is characterized in that described Absorption Refrigerator (8) is provided with the cooling medium entrance and links to each other respectively with the cooling medium outlet that combustion machine entrance cooler (1) and inter cooler (3) are provided with, cooling medium is done closed cycle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012104056740A CN102900531A (en) | 2012-10-23 | 2012-10-23 | Combustion gas turbine system with inlet cooling and indirect cooling |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012104056740A CN102900531A (en) | 2012-10-23 | 2012-10-23 | Combustion gas turbine system with inlet cooling and indirect cooling |
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| CN102900531A true CN102900531A (en) | 2013-01-30 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2012104056740A Pending CN102900531A (en) | 2012-10-23 | 2012-10-23 | Combustion gas turbine system with inlet cooling and indirect cooling |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103195577A (en) * | 2013-04-11 | 2013-07-10 | 重庆大学 | Air intake temperature regulating system of gas turbine |
| CN103574982A (en) * | 2013-10-29 | 2014-02-12 | 清华大学 | Efficient cleaning and refrigerating system based on miniature gas turbine |
| CN107100736A (en) * | 2017-06-09 | 2017-08-29 | 厦门大学 | Combustion turbine combined system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2003206752A (en) * | 2002-01-17 | 2003-07-25 | Mitsubishi Heavy Ind Ltd | Gas turbine equipment |
| CN201002715Y (en) * | 2006-12-14 | 2008-01-09 | 上海交通大学 | Gas turbine Stirling engine electric propulsion device for large-scale vessels high speed sailing |
| CN101503975A (en) * | 2009-03-18 | 2009-08-12 | 哈尔滨工业大学 | Main pipe type micro turbine group of dual-air compressor |
| US20110088399A1 (en) * | 2009-10-15 | 2011-04-21 | Briesch Michael S | Combined Cycle Power Plant Including A Refrigeration Cycle |
| CN202811077U (en) * | 2012-10-23 | 2013-03-20 | 中国船舶重工集团公司第七�三研究所 | Gas turbine system with inlet cooling and intercooling functions |
-
2012
- 2012-10-23 CN CN2012104056740A patent/CN102900531A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2003206752A (en) * | 2002-01-17 | 2003-07-25 | Mitsubishi Heavy Ind Ltd | Gas turbine equipment |
| CN201002715Y (en) * | 2006-12-14 | 2008-01-09 | 上海交通大学 | Gas turbine Stirling engine electric propulsion device for large-scale vessels high speed sailing |
| CN101503975A (en) * | 2009-03-18 | 2009-08-12 | 哈尔滨工业大学 | Main pipe type micro turbine group of dual-air compressor |
| US20110088399A1 (en) * | 2009-10-15 | 2011-04-21 | Briesch Michael S | Combined Cycle Power Plant Including A Refrigeration Cycle |
| CN202811077U (en) * | 2012-10-23 | 2013-03-20 | 中国船舶重工集团公司第七�三研究所 | Gas turbine system with inlet cooling and intercooling functions |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103195577A (en) * | 2013-04-11 | 2013-07-10 | 重庆大学 | Air intake temperature regulating system of gas turbine |
| CN103195577B (en) * | 2013-04-11 | 2015-08-26 | 重庆大学 | Gas turbine air inlet temperature regulating system |
| CN103574982A (en) * | 2013-10-29 | 2014-02-12 | 清华大学 | Efficient cleaning and refrigerating system based on miniature gas turbine |
| CN107100736A (en) * | 2017-06-09 | 2017-08-29 | 厦门大学 | Combustion turbine combined system |
| CN107100736B (en) * | 2017-06-09 | 2019-08-27 | 厦门大学 | Combustion turbine combined system |
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Application publication date: 20130130 |