CN105484870A - Combined-cycle gas turbine system - Google Patents

Combined-cycle gas turbine system Download PDF

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Publication number
CN105484870A
CN105484870A CN201511007963.5A CN201511007963A CN105484870A CN 105484870 A CN105484870 A CN 105484870A CN 201511007963 A CN201511007963 A CN 201511007963A CN 105484870 A CN105484870 A CN 105484870A
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CN
China
Prior art keywords
gas
regenerator
runner
turbine
gas turbine
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
Application number
CN201511007963.5A
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Chinese (zh)
Inventor
李孝堂
胡云彪
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
AECC Shenyang Engine Research Institute
AVIC Shenyang Engine Design and Research Institute
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AVIC Shenyang Engine Design and Research Institute
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Publication date
Application filed by AVIC Shenyang Engine Design and Research Institute filed Critical AVIC Shenyang Engine Design and Research Institute
Priority to CN201511007963.5A priority Critical patent/CN105484870A/en
Publication of CN105484870A publication Critical patent/CN105484870A/en
Pending legal-status Critical Current

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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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use
    • F02C6/18—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
    • F01K25/00—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for
    • F01K25/08—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for using special vapours
    • F01K25/14—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for using special vapours using industrial or other waste gases
    • 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
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E20/00—Combustion technologies with mitigation potential
    • Y02E20/14—Combined heat and power generation [CHP]

Abstract

The invention relates to the design of gas turbines, in particular to a combined-cycle gas turbine system which at least solves the problem that ash is easily deposited during gas exhaust waste heat utilization of a current gas turbine. The combined-cycle gas turbine system comprises a first gas turbine, a first cooling water tube and a second gas turbine, wherein the first gas turbine is provided with a first gas compressor and a first worm; gas flow flowing out from the gas outlet of the first gas compressor flows into the gas inlet of the first worm through a first heat regenerator; gas flow flowing out from the gas outlet of the first worm flows into the gas inlet of the first gas compressor through a second heat regenerator; the first cooling water tube is communicated with the second heat regenerator; the second gas turbine is provided with a second gas compressor, a combustion chamber and a second worm which are sequentially communicated; gas flow flowing out from the gas outlet of the second worm flows through the first heat regenerator, and is used for heating gas flow flowing into the heat regenerator from the gas outlet of the first gas compressor. The combined-cycle gas turbine system adopts a closed-cycle working medium which is sealed inside a closed-cycle gas turbine, and does not have an ash deposition problem, so that the system stability is stronger.

Description

A kind of combined cycle gas turbine system
Technical field
The present invention relates to gas turbine design, particularly relate to a kind of combined cycle gas turbine system.
Background technique
In the gas turbine, air is compressed, burning, delivery temperature after acting are still very high, and having a large amount of exhaust heats can utilize, and existing heat recovery technology is all based on open cycle, is difficult to the dust stratification, oxide etch etc. of avoiding heat recovery parts.
Summary of the invention
The object of this invention is to provide a kind of combined cycle gas turbine system, at least solve the problem of easy dust stratification during existing combustion turbine exhaustion UTILIZATION OF VESIDUAL HEAT IN.
Technological scheme of the present invention is:
A kind of combined cycle gas turbine system, comprising:
First combustion engine, described first combustion engine has the first gas compressor and the first turbine;
First regenerator, the air-flow that described first gas compressor air outlet is flowed out flows into described first turbine air-intake by described first regenerator;
Second regenerator, the air-flow that described first turbine air outlet is flowed out flows into described first compressor air inlet machine mouth by described second regenerator;
First water-cooling tube, is communicated with described second regenerator, for being cooled the air-flow flowed through in described second regenerator by cooling water;
Second combustion engine, described second combustion engine has and is communicated with the second gas compressor, firing chamber and the second turbine successively, first regenerator described in the airflow passes that described second turbine air outlet is flowed out, heats for the air-flow flowed in described first regenerator described first gas compressor air outlet.
Preferably, described first combustion engine also comprises:
3rd gas compressor, the air outlet of described first turbine is communicated with the suction port of described 3rd gas compressor by described second regenerator;
3rd regenerator, the air outlet of described 3rd gas compressor is communicated with the suction port of described first gas compressor by described 3rd regenerator;
Second water-cooling tube, is communicated with described 3rd regenerator, for being cooled the air-flow flowed through in described 3rd regenerator by cooling water.
Preferably, described first regenerator inside has the first flow and the second runner that are parallel to each other, described first gas compressor air outlet is communicated with described first turbine air-intake by described first flow, and described second turbine air outlet is in communication with the outside by described second runner.
Preferably, described first flow is contrary with airflow direction in the second runner.
Preferably, described second regenerator inside has the 3rd runner and the 4th runner that are parallel to each other, and described first turbine air outlet is communicated with described first compressor air inlet machine mouth by described 3rd runner, and the first water-cooling tube is in communication with the outside by described 4th runner.
Preferably, in described 3rd runner, the direction of air-flow is contrary with the flow direction of cooling water in described 4th runner.
Preferably, described 3rd regenerator inside has the 5th runner and the 6th runner that are parallel to each other, the air outlet of described 3rd gas compressor is communicated with described first compressor air inlet machine mouth by described 5th runner, and the second water-cooling tube is in communication with the outside by described 6th runner.
Preferably, in described 5th runner, the direction of air-flow is contrary with the flow direction of cooling water in described 6th runner.
The invention has the advantages that:
Combined cycle gas turbine system of the present invention, forms closed circulation system between the first combustion engine and the second combustion engine, adopts closed cycle working medium to be enclosed in closed cycle combustion engine inner, there is not dust stratification problem, make the stability of a system stronger.
Accompanying drawing explanation
Fig. 1 is the structural representation of a combined cycle gas turbine system of the present invention preferred embodiment;
Fig. 2 be in Fig. 1 combined cycle gas turbine system improve further after structural representation.
Embodiment
For making object of the invention process, technological scheme and advantage clearly, below in conjunction with the accompanying drawing in the embodiment of the present invention, the technological scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Described embodiment is the present invention's part embodiment, instead of whole embodiments.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the present invention, and can not limitation of the present invention be interpreted as.Based on the embodiment in the present invention, those of ordinary skill in the art, not making the every other embodiment obtained under creative work prerequisite, belong to the scope of protection of the invention.Below in conjunction with accompanying drawing, embodiments of the invention are described in detail.
In describing the invention, it will be appreciated that, term " " center ", " longitudinal direction ", " transverse direction ", " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end ", " interior ", orientation or the position relationship of the instruction such as " outward " are based on orientation shown in the drawings or position relationship, only the present invention for convenience of description and simplified characterization, instead of indicate or imply that the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore limiting the scope of the invention can not be interpreted as.
Below in conjunction with accompanying drawing 1 to Fig. 2, combined cycle gas turbine system of the present invention is described in further details.
The invention provides a kind of combined cycle gas turbine system, comprise the first combustion engine (Fig. 1 and Fig. 2 lower middle portion, for closed cycle combustion engine), (Fig. 1 and Fig. 2 divides middle and upper part the second combustion engine, for open cycle combustion engine, be inlet end on the left of it), the first regenerator 31 and the second regenerator 32.
First combustion engine has the first gas compressor 11 and the first turbine 12, first turbine 12 connects corresponding load; The air-flow that first gas compressor 11 air outlet is flowed out flows into the first turbine 12 suction port by the first regenerator 31.The air-flow that first turbine 11 air outlet is flowed out flows into the first gas compressor 11 suction port by the second regenerator 32.In addition, also comprise the first water-cooling tube 41, first water-cooling tube 41 and be communicated with the second regenerator 32, for being cooled the air-flow flowed through in the second backheat 32 device by cooling water.
Second combustion engine has and is communicated with the second gas compressor 21, firing chamber 22 and the second turbine 23, second turbine 23 successively and connects corresponding load; In addition, airflow passes first regenerator 31 that the second turbine 23 air outlet is flowed out, heats for the air-flow flowed in the first regenerator 31 the first gas compressor 11 air outlet.
Combined cycle gas turbine system of the present invention, adopts above-mentioned linkage structure between the first combustion engine and the second combustion engine, forms closed circulation system, and it is inner that cycle fluid is enclosed in closed cycle combustion engine, there is not dust stratification problem, make the stability of a system stronger.
By adopting closed cycle to improve or to reduce round-robin basis pressure, can by selecting suitable closed cycle pressure of foundation to obtain higher income.Such as, when improving round-robin basis pressure, combustion engine size can be reduced, effectively reducing unit weight, reducing costs; When reducing round-robin basis pressure, effectively can reduce the leakage of blade, improving the efficiency of gas compressor and turbine, improve the income of unit.
In addition, cycle fluid wherein can adopt multiple applicable gas as required, in the present embodiment, preferably adopts nitrogen, helium etc. as closed cycle working medium, can avoid the oxide etch of parts, improves combustion engine reliability, extends the combustion engine life-span.
Further, by the Cooling Design of the first regenerator 31 and the second regenerator 32, cold between realizing between compressor stage, can power input to compressor be reduced, improve closed-cycle turbine power stage, improve the power of the assembling unit and the thermal efficiency.The turbine outlet exhaust waste heat of closed cycle is all taken away by regenerator, is retained in cooling water, and this part waste heat can be used as heat supply, follow-uply can realize cogeneration, and cogeneration efficiency can reach 71%.
Further, in combined cycle gas turbine system of the present invention, the first combustion engine also comprises the 3rd gas compressor 13, the 3rd regenerator 33 and the second water-cooling tube 42.
The air outlet of the first turbine 12 is communicated with the suction port of the 3rd gas compressor 13 by the second regenerator 32; The air outlet of the 3rd gas compressor 13 is communicated with the suction port of the first gas compressor 11 by the 3rd regenerator 33; Second water-cooling tube 42 is communicated with the 3rd regenerator 33, for being cooled the air-flow flowed through in the 3rd regenerator 33 by cooling water.
In combined cycle gas turbine system of the present invention, regenerator can adopt known multiple applicable structure; In the present embodiment, the first regenerator 31 inside has the first flow and the second runner that are parallel to each other, and the first gas compressor 11 air outlet is communicated with the first turbine 12 suction port by first flow, and the second turbine 23 air outlet is in communication with the outside by the second runner; Further, first flow is contrary with airflow direction in the second runner.
Equally, the second regenerator 32 inside has the 3rd runner and the 4th runner that are parallel to each other, and the first turbine 12 air outlet is communicated with described first gas compressor 11 suction port by the 3rd runner, and the first water-cooling tube 41 is in communication with the outside by described 4th runner; In 3rd runner, the direction of air-flow is contrary with the flow direction of cooling water in the 4th runner.
3rd regenerator 33 inside has the 5th runner and the 6th runner that are parallel to each other, and the air outlet of the 3rd gas compressor 13 is communicated with the first gas compressor 11 suction port by the 5th runner, and the second water-cooling tube 42 is in communication with the outside by the 6th runner; In 5th runner, the direction of air-flow is contrary with the flow direction of cooling water in the 6th runner.
In combined cycle gas turbine system of the present invention, gas compressor compression unit mass air consumption merit can be calculated by following formula (1):
L k = k k - 1 RT B * π k * k - 1 k - 1 η k * = k k - 1 R ( T k * - T B * ) ...... ( 1 ) ;
Wherein, Lk is unit quality air compression wasted work, and k is adiabatic index, and R is gas constant, and TB* is compressor inlet stagnation temperature, and π k* is compressor pressure ratio, and η k* is compressor efficiency, and Tk* is blower outlet stagnation temperature.
Further, turbine expansion unit mass air is sent merit and can be calculated by following formula (2):
L r = k r k r - 1 R r T r * ( 1 - 1 π T * k r - 1 k r ) η T * = k r k r - 1 R r ( T r * - T T * ) ...... ( 2 ) ;
Wherein, Lr is unit quality air expansion work, and kr is adiabatic index, and R is gas constant, and Tr* is turbine inlet turbine stagnation temperature, and π T* is expansion ratio of turbine, and η T* is turbine efficiency, TT* turbine outlet stagnation temperature.
Firing chamber oil-gas ratio can be calculated by following formula (3):
f = i a 3 * - i a 2 * ηH μ + ΔI f + H 0 - H 3 * ...... ( 3 ) ;
Wherein, f is oil-gas ratio, ia3* is outlet air enthalpy (under outlet temperature unit quality air enthalpy), ia2* is intake air enthalpy (under inlet temperature unit quality air enthalpy), and η is combustion efficiency, and H μ is lower calorific value of fuel (calorific value when products of combustion is water vapour), Δ if is that (temperature difference takes advantage of mean specific heat to the fuel enthalpy difference that causes of temperature difference, generally ignore), H0 is the enthalpy difference at fuel inlet temperature, and H3* is enthalpy difference.
Existing open cycle combustion engine part calculating parameter is as follows:
Intake temperature 288K, flow 20kg/s, pressure ratio 15, combustor exit temperature 1500K, fuel value 42700kJ/kg.Can be calculated combustion engine power 5764kw, the thermal efficiency 32%.
In invention specific embodiment, particularly adopt the structure shown in Fig. 2, closed cycle combustion engine part calculating parameter is:
Intake temperature 296K (iterative value), flow 20kg/s, overall pressure tatio 5, heat exchanger cooling water temperature 291K, the regenerator effectiveness of the second regenerator (32) and the 3rd regenerator (33) is 0.85.Can be calculated closed cycle combustion engine power 1452kw, total output 7216kw, improve 25%, overall thermal efficiency 40%, improve 25%.If consider, the heat that closed cycle combustion engine heat exchanger cooling water reclaims is used for heat supply, then can produce 5558kw heating power, cogeneration efficiency can reach 71%.Shown by above-mentioned calculating, combined cycle gas turbine can significantly improve power and the thermal efficiency of combustion engine, especially has very high cogeneration efficiency, has good development prospect.
The above; be only the specific embodiment of the present invention, but protection scope of the present invention is not limited thereto, is anyly familiar with those skilled in the art in the technical scope that the present invention discloses; the change that can expect easily or replacement, all should be encompassed within protection scope of the present invention.Therefore, protection scope of the present invention should be as the criterion with the protection domain of described claim.

Claims (8)

1. a combined cycle gas turbine system, is characterized in that, comprising:
First combustion engine, described first combustion engine has the first gas compressor (11) and the first turbine (12);
First regenerator (31), the air-flow that described first gas compressor (11) air outlet is flowed out flows into described first turbine (12) suction port by described first regenerator (31);
Second regenerator (32), the air-flow that described first turbine (11) air outlet is flowed out flows into described first gas compressor (11) suction port by described second regenerator (32);
First water-cooling tube (41), is communicated with described second regenerator (32), for being cooled the air-flow flowed through in described second backheat (32) device by cooling water;
Second combustion engine, described second combustion engine has and is communicated with the second gas compressor (21), firing chamber (22) and the second turbine (23) successively, first regenerator (31) described in the airflow passes that described second turbine (23) air outlet is flowed out, heats for the air-flow flowed in described first regenerator (31) described first gas compressor (11) air outlet.
2. combined cycle gas turbine system according to claim 1, is characterized in that, described first combustion engine also comprises:
3rd gas compressor (13), the air outlet of described first turbine (12) is communicated with the suction port of described 3rd gas compressor (13) by described second regenerator (32);
3rd regenerator (33), the air outlet of described 3rd gas compressor (13) is communicated with the suction port of described first gas compressor (11) by described 3rd regenerator (33);
Second water-cooling tube (42), is communicated with described 3rd regenerator (33), for being cooled the air-flow flowed through in described 3rd regenerator (33) by cooling water.
3. combined cycle gas turbine system according to claim 2, it is characterized in that, described first regenerator (31) inside has the first flow and the second runner that are parallel to each other, described first gas compressor (11) air outlet is communicated with described first turbine (12) suction port by described first flow, and described second turbine (23) air outlet is in communication with the outside by described second runner.
4. combined cycle gas turbine system according to claim 3, is characterized in that, described first flow is contrary with airflow direction in the second runner.
5. combined cycle gas turbine system according to claim 2, it is characterized in that, described second regenerator (32) inside has the 3rd runner and the 4th runner that are parallel to each other, described first turbine (12) air outlet is communicated with described first gas compressor (11) suction port by described 3rd runner, and the first water-cooling tube (41) is in communication with the outside by described 4th runner.
6. combined cycle gas turbine system according to claim 5, is characterized in that, in described 3rd runner, the direction of air-flow is contrary with the flow direction of cooling water in described 4th runner.
7. combined cycle gas turbine system according to claim 2, it is characterized in that, described 3rd regenerator (33) inside has the 5th runner and the 6th runner that are parallel to each other, the air outlet of described 3rd gas compressor (13) is communicated with described first gas compressor (11) suction port by described 5th runner, and the second water-cooling tube (42) is in communication with the outside by described 6th runner.
8. combined cycle gas turbine system according to claim 7, is characterized in that, in described 5th runner, the direction of air-flow is contrary with the flow direction of cooling water in described 6th runner.
CN201511007963.5A 2015-12-29 2015-12-29 Combined-cycle gas turbine system Pending CN105484870A (en)

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Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN86104890A (en) * 1986-07-31 1988-02-10 通用电气公司 The thermodynamic conversion system of air circulation
CN1048911A (en) * 1989-05-29 1991-01-30 透勃康塞脱有限公司 The method and apparatus of generating
CN1220341A (en) * 1997-12-17 1999-06-23 亚瑞亚·勃朗勃威力有限公司 Gas/steam generating equipment
CN101761389A (en) * 2010-01-15 2010-06-30 绍兴文理学院 Circulatory thermal power generation method and device of working medium phase-change gas turbine
CN101906998A (en) * 2009-07-31 2010-12-08 王世英 Multi-cycle electricity-generation thermodynamic system and implementing method thereof
CN102345511A (en) * 2010-07-23 2012-02-08 通用电气公司 A hybrid power generation system and a method thereof
CN104806356A (en) * 2015-04-27 2015-07-29 南京瑞柯徕姆环保科技有限公司 Cascaded Bretton combined cycle power generation method and device

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN86104890A (en) * 1986-07-31 1988-02-10 通用电气公司 The thermodynamic conversion system of air circulation
CN1048911A (en) * 1989-05-29 1991-01-30 透勃康塞脱有限公司 The method and apparatus of generating
CN1220341A (en) * 1997-12-17 1999-06-23 亚瑞亚·勃朗勃威力有限公司 Gas/steam generating equipment
CN101906998A (en) * 2009-07-31 2010-12-08 王世英 Multi-cycle electricity-generation thermodynamic system and implementing method thereof
CN101761389A (en) * 2010-01-15 2010-06-30 绍兴文理学院 Circulatory thermal power generation method and device of working medium phase-change gas turbine
CN102345511A (en) * 2010-07-23 2012-02-08 通用电气公司 A hybrid power generation system and a method thereof
CN104806356A (en) * 2015-04-27 2015-07-29 南京瑞柯徕姆环保科技有限公司 Cascaded Bretton combined cycle power generation method and device

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Application publication date: 20160413