CN105221263A - Cold Gas Turbine Combined-cycle system between one - Google Patents
Cold Gas Turbine Combined-cycle system between one Download PDFInfo
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- CN105221263A CN105221263A CN201510600405.3A CN201510600405A CN105221263A CN 105221263 A CN105221263 A CN 105221263A CN 201510600405 A CN201510600405 A CN 201510600405A CN 105221263 A CN105221263 A CN 105221263A
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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
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E20/00—Combustion technologies with mitigation potential
- Y02E20/16—Combined cycle power plant [CCPP], or combined cycle gas turbine [CCGT]
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Abstract
The invention discloses cold Gas Turbine Combined-cycle system between one, relate to gas turbine technology field.Described cold Gas Turbine Combined-cycle system, comprise exhaust heat boiler, low pressure compressor, high-pressure turbine, high-pressure compressor, containing turbine assembly, afterburning firing chamber and interstage cooler, wherein, described afterburning combustion chamber placement is between high-pressure turbine and turbine assembly, the combustion gas that high-pressure turbine is discharged adds turbine assembly after afterburning firing chamber is heated again, and the delivery temperature of turbine assembly raises; The exhaust end of described turbine assembly is connected with the inlet end of described exhaust heat boiler; Described interstage cooler is arranged between low pressure compressor and high-pressure compressor.Usefulness of the present invention is: add afterburning firing chamber in cold Gas Turbine Combined-cycle system between in the present invention, and the gas temperature that low-pressure turbine and power turbine assembly are discharged is higher, improves the efficiency of exhaust heat boiler.
Description
Technical field
The present invention relates to gas turbine technology field, be specifically related to cold Gas Turbine Combined-cycle system between one.
Background technique
Between SAPMAC method gas turbine be on the basis of simple cycle, increase compressed-air intercooler composition complex-cycle gas turbine, owing to adding cooling during rolling, make its efficiency comparatively simple cycle gas turbine engine get a promotion.
In the gas turbine, between employing, the gas turbine of SAPMAC method is due to its high cycle ratio merit and high efficiency, day by day receives the concern of people.But between routine in SAPMAC method gas turbine, combustion gas is after high-pressure turbine expansion work, and temperature declines.In waste heat boiler type combined cycle, the exhaust of gas turbine passes in exhaust heat boiler, the water generates steam driving steam turbine acting in heating boiler.But the gas temperature that gas turbine medium power turbine is discharged is lower, causes based on the Gas Turbine Combined-cycle thermal efficiency cold between combined cycle lower (between GE company of the U.S. the cold Gas Turbine Combined-cycle LSM100PA thermal efficiency 50.1%).
Summary of the invention
The object of this invention is to provide cold Gas Turbine Combined-cycle system between one, with the problem that the thermal efficiency in cold Gas Turbine Combined-cycle system between solving in background technique is lower.
Technological scheme of the present invention is: provide cold Gas Turbine Combined-cycle system between one, comprise exhaust heat boiler, low pressure compressor, high-pressure turbine, high-pressure compressor, turbine assembly, afterburning firing chamber and interstage cooler, wherein, described afterburning combustion chamber placement is between high-pressure turbine and turbine assembly, the combustion gas that high-pressure turbine is discharged adds turbine assembly after afterburning firing chamber is heated again, and the delivery temperature of turbine assembly raises; The exhaust end of described turbine assembly is connected with the inlet end of described exhaust heat boiler; Described interstage cooler is arranged between low pressure compressor and high-pressure compressor.
Preferably, described cold Gas Turbine Combined-cycle system comprises the first rotor, the second rotor, low pressure compressor and high-pressure compressor further, wherein, described low pressure compressor is connected by the first rotor with turbine assembly, and low pressure compressor is coaxial with turbine assembly, described high-pressure turbine is connected by the second rotor with between high-pressure compressor, and high-pressure turbine is coaxial with high-pressure compressor.
Preferably, described turbine assembly comprises low-pressure turbine and power turbine, and combustion gas enters low-pressure turbine after burning again in afterburning firing chamber, and combustion gas is expansion work rear driving power turbine in low-pressure turbine.
Preferably, one end of described the first rotor is for connecting the second load, and described low pressure compressor is arranged between described turbine assembly and the second load.
Preferably, the inlet end of described low pressure compressor deviates from the exhaust end of turbine assembly.
Preferably, described low pressure compressor is arranged along the axisymmetrical of the first rotor with the vane foil of rotation direction.
Preferably, described turbine assembly drives low pressure compressor and the second load simultaneously.
Beneficial effect of the present invention: add afterburning firing chamber in cold Gas Turbine Combined-cycle system between in the present invention, the gas temperature that low-pressure turbine and power turbine assembly are discharged is higher, improves the efficiency of exhaust heat boiler.
Accompanying drawing explanation
The schematic diagram of cold Gas Turbine Combined-cycle system between Fig. 1 one embodiment of the invention.
Wherein: 1-first load, 2-steam turbine, 3-exhaust heat boiler, 4-second load, 5-the first rotor, 6-low pressure compressor, 7-turbine assembly, 8-afterburning firing chamber, 9-high-pressure turbine, 10-firing chamber, 11-high-pressure compressor, 12-second rotor, 13-interstage cooler.
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", "rear", "left", "right", " vertically ", " level ", " top ", " end " " interior ", " outward " etc. instruction orientation or position relationship be based on orientation shown in the drawings or position relationship; be only the present invention for convenience of description and simplified characterization; instead of instruction or imply indication device or element must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as limiting the scope of the invention.
As shown in Figure 1, cold Gas Turbine Combined-cycle system between one, include the first load 1, steam turbine 2, exhaust heat boiler 3, second load 4, second rotor 5, low pressure compressor 6, turbine assembly 7, afterburning firing chamber 8, high-pressure turbine 9, firing chamber 10, high-pressure compressor 11, second rotor 12 and interstage cooler 13, wherein, turbine assembly 7 comprises low-pressure turbine and power turbine, combustion gas enters low-pressure turbine after burning again in afterburning firing chamber 8, and combustion gas is expansion work rear driving power turbine in low-pressure turbine.
Low pressure compressor 6 is connected by the first rotor 5 with turbine assembly 7, and low pressure compressor 6 is coaxial with turbine assembly 7, and one end of the first rotor 5 is for connecting the second load 4.
Low-pressure turbine and power turbine compared to existing technology, are assembled into turbine assembly 7 by the present invention.Turbine assembly 7 is energize low-pressure gas compressor 6 and the second load 4 simultaneously, decreases the quantity of part, shorten the axial length of the first rotor 5, improve the reliability of system.
Low pressure compressor 6 is arranged between turbine assembly 7 and the second load 4, and the inlet end of low pressure compressor 6 is away from the exhaust end of turbine assembly 7 (in accompanying drawing 1, the right-hand member of low pressure compressor 6 is the inlet end of low pressure compressor 6, and the right-hand member of turbine assembly 7 is the exhaust end of turbine assembly 7).Low pressure compressor 6 with rotation direction vane foil along the axisymmetrical of the first rotor 5 arrange obtain derotation to vane foil, make the airflow direction of turbine assembly 7 and low pressure compressor 6 contrary, and rotation direction is identical.
The inlet end of low pressure compressor 6 is away from the advantage of the exhaust end of turbine assembly 7: the inlet temperature of low pressure compressor 6, by the impact of the exhaust of turbine assembly 7, improves the air quality of low pressure compressor 6 import.
High-pressure turbine 9 is connected by the second rotor 12 with high-pressure compressor 11, and high-pressure turbine 9 is coaxial with high-pressure compressor 11, is furnished with firing chamber 10 between high-pressure turbine 9 and high-pressure compressor 11, and high-pressure compressor 11 will enter firing chamber 10 after air compressing.In firing chamber 10, spray into fuel, fuel burns and generates high-temperature high-pressure fuel gas under high-pressure air, and high-temperature high-pressure fuel gas flows into high-pressure turbine 9 and does work for high-pressure turbine 9, and high-pressure turbine 9 is done work and is used for being operated by the second rotor 12 energizes high-pressure gas compressor 11.
The present invention compared to existing technology, include the first rotor 5 and the second rotor 12, its advantage is: rotor of the prior art needs through interstage cooler 13, high-pressure compressor 11, firing chamber 10, high-pressure turbine 9, the axial distance of rotor is longer, is unfavorable for that rotor bearing is arranged and rotor dynamics design.And in the present invention, have employed two rotors, rotor axial length obviously reduces, and significantly improves the rigidity of rotor, is conducive to the dynamics Design of rotor, makes in gas turbine working procedure more stable.
Afterburning firing chamber 8 is arranged between the high-pressure turbine 9 on the second rotor 12 and the turbine assembly 7 on the first rotor 5.Afterburning firing chamber 8 is heated again to the combustion gas of flowing out from high-pressure turbine 9, fuel is sprayed in afterburning firing chamber 8, Thorough combustion in the high-temperature high-pressure air flow of fuel in afterburning firing chamber 8, combustion gas after burning flows into turbine assembly 7 and does work, and turbine assembly 7 is by the first rotor 5 energize low-pressure gas compressor 6 and the second load 4.
The advantage increasing afterburning firing chamber 8 is: the temperature that can improve turbine assembly 7 inlet gas, the circulation merit of gas turbine is strengthened, and pressure in afterburning firing chamber 8 is higher, combustion efficiency is also high, thus the level that not only improve power but also made the thermal efficiency keep higher, to reduction pollutant emission, reduce engine cooling tolerance, to improve gas turbine Security etc. very favourable.
After afterburning firing chamber 8 is heated again to the combustion gas of flowing out from high-pressure turbine 9, the delivery temperature of turbine assembly 7 is higher, the exhaust end of turbine assembly 7 is connected with the inlet end of exhaust heat boiler 3, after the exhaust of turbine assembly 7 enters exhaust heat boiler 3, water vapour is become to the water heating in exhaust heat boiler 3, water vapour drives steam turbine 2 do work and drive the first load 1, and the water that water vapour condenses into after expanding in steam turbine 2 and doing manual work stays back exhaust heat boiler 3 again.
Interstage cooler 13 is arranged between low pressure compressor 6 and high-pressure compressor 11, and air, after low pressure compressor 6 compresses, enters high-pressure compressor 11 by interstage cooler 13.Interstage cooler 13 reduces temperature when air enters high-pressure compressor 11, and therefore the compression wasted work of high-pressure compressor 11 reduces, and the specific power of whole unit is improved.
The power of of the present invention cold Gas Turbine Combined-cycle system can improve 105% compared to existing technology, and the thermal efficiency improves 58.5%.
Its formula is:
Gas compressor compression unit mass air consumption merit:
Wherein:
L
kfor unit quality air compression wasted work, k is adiabatic index,
R is gas constant,
for compressor inlet stagnation temperature
for compressor pressure ratio,
for compressor efficiency
for blower outlet stagnation temperature;
Turbine expansion unit mass air sends merit:
Wherein:
L
runit mass air expansion work, k
rfor adiabatic index
R is gas constant,
for turbine inlet turbine stagnation temperature
for expansion ratio of turbine,
for turbine efficiency
for turbine outlet stagnation temperature;
Firing chamber oil-gas ratio:
Wherein:
F is oil-gas ratio,
for outlet air enthalpy (under outlet temperature unit quality air enthalpy),
η is combustion efficiency,
for intake air enthalpy (under inlet temperature unit quality air enthalpy),
for enthalpy difference, H
μfor lower calorific value of fuel (calorific value when products of combustion is water vapour),
Δ I
ffor the fuel enthalpy difference (temperature difference takes advantage of mean specific heat, generally ignores) that temperature difference causes,
H
0for the enthalpy difference at fuel inlet temperature.
Suppose that the intake temperature of prior art mesolow gas compressor is 288K, flow is 100kg/s, low pressure pressure ratio is 4, interstage cooler water temperature is 291K, and interstage cooler efficiency is 0.85, and high pressure pressure ratio is 12, combustor exit temperature is 1600K, fuel value 42700KJ/kg, can obtain combustion engine power is as calculated 39493KW, and the thermal efficiency is 42.3%., before power turbine, temperature is 998K, and delivery temperature is 657K.
And under identical assumed condition, between in the present invention, cold Gas Turbine Combined-cycle system-computed parameter is: the intake temperature of low pressure compressor is 288K, flow is 100kg/s, low pressure pressure ratio is 4, interstage cooler water temperature is 291K, interstage cooler efficiency is 0.85, high pressure pressure ratio is 12, combustor exit temperature is 1600K, fuel value is 42700KJ/kg, afterburning combustor exit temperature is 1600K, afterburning burner efficiency is 0.97, afterburning combustor total pressure recovery factor is 0.975, high-pressure turbine, low-pressure turbine air conditioning quantity is 10%, can obtain combustion engine power is as calculated 58984KW, before power turbine, temperature is 1382K, delivery temperature is 891K, in combined cycle, steam turbine Partial Power is 21928KW, total output is 80912KW, total output compared to existing technology improves 105%, overall thermal efficiency is 58.5%.
Contrast shows as calculated, and a cold Gas Turbine Combined-cycle system can significantly improve power and the thermal efficiency of gas turbine.
Finally it is to be noted: above embodiment only in order to technological scheme of the present invention to be described, is not intended to limit.Although with reference to previous embodiment to invention has been detailed description, those of ordinary skill in the art is to be understood that: it still can be modified to the technological scheme described in foregoing embodiments, or carries out equivalent replacement to wherein portion of techniques feature; And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of various embodiments of the present invention technological scheme.
Claims (7)
1. cold Gas Turbine Combined-cycle system between a kind, comprise exhaust heat boiler (3), low pressure compressor (6), high-pressure turbine (9) and high-pressure compressor (11), it is characterized in that: comprise turbine assembly (7), afterburning firing chamber (8) and interstage cooler (13) further, wherein
Described afterburning firing chamber (8) is arranged between high-pressure turbine (9) and turbine assembly (7), the combustion gas that high-pressure turbine (9) is discharged adds turbine assembly (7) after afterburning firing chamber (8) heat again, and the delivery temperature of turbine assembly (7) raises;
The exhaust end of described turbine assembly (7) is connected with the inlet end of described exhaust heat boiler (3);
Described interstage cooler (13) is arranged between low pressure compressor (6) and high-pressure compressor (11).
2. according to claim 1 cold Gas Turbine Combined-cycle system, it is characterized in that: between described, cold Gas Turbine Combined-cycle system comprises the first rotor (5), the second rotor (12), low pressure compressor (6) and high-pressure compressor (11) further, wherein
Described low pressure compressor (6) is connected by the first rotor (5) with turbine assembly (7), and low pressure compressor (6) is coaxial with turbine assembly (7), be connected by the second rotor (12) between described high-pressure turbine (9) with high-pressure compressor (11), and high-pressure turbine (9) is coaxial with high-pressure compressor (11).
3. according to claim 1 cold Gas Turbine Combined-cycle system, it is characterized in that: described turbine assembly (7) comprises low-pressure turbine and power turbine, combustion gas enters low-pressure turbine after afterburning firing chamber (8) burn again, and combustion gas is expansion work rear driving power turbine in low-pressure turbine.
4. according to claim 2 cold Gas Turbine Combined-cycle system, it is characterized in that: one end of described the first rotor (5) is for connecting the second load (4), and described low pressure compressor (6) is arranged between described turbine assembly (7) and the second load (4).
5. according to claim 4 cold Gas Turbine Combined-cycle system, is characterized in that: the inlet end of described low pressure compressor (6) deviates from the exhaust end of turbine assembly (7).
6. according to claim 4 cold Gas Turbine Combined-cycle system, is characterized in that: described low pressure compressor (6) is arranged along the axisymmetrical of the first rotor (5) with the vane foil of rotation direction.
7. according to claim 4 cold Gas Turbine Combined-cycle system, is characterized in that: described turbine assembly (7) drives low pressure compressor (6) and the second load (4) simultaneously.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510600405.3A CN105221263A (en) | 2015-09-18 | 2015-09-18 | Cold Gas Turbine Combined-cycle system between one |
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| CN201510600405.3A CN105221263A (en) | 2015-09-18 | 2015-09-18 | Cold Gas Turbine Combined-cycle system between one |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107575310A (en) * | 2017-10-24 | 2018-01-12 | 江苏华强新能源科技有限公司 | A kind of high-efficiency gas turbine air outlet temperature regulating system |
| CN108954374A (en) * | 2018-08-16 | 2018-12-07 | 哈尔滨锅炉厂有限责任公司 | Combined Cycle Heat Recovery Boiler afterburning wind system |
| CN115324731A (en) * | 2022-08-16 | 2022-11-11 | 星辰萌想科技(北京)有限公司 | Gas turbine |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4896499A (en) * | 1978-10-26 | 1990-01-30 | Rice Ivan G | Compression intercooled gas turbine combined cycle |
| CN1165238A (en) * | 1996-04-22 | 1997-11-19 | 亚瑞亚·勃朗勃威力有限公司 | Operation method for combined equipment |
| CN103608567A (en) * | 2011-07-07 | 2014-02-26 | 俄罗斯铁路开放式股份公司 | Gas turbine arrangement for a locomotive |
| WO2015038768A1 (en) * | 2013-09-12 | 2015-03-19 | Florida Turbine Technologies, Inc. | High pressure ratio twin spool industrial gas turbine engine |
| EP2915963A1 (en) * | 2014-03-05 | 2015-09-09 | Siemens Aktiengesellschaft | Cogeneration plant and method to operate a cogeneration plant |
-
2015
- 2015-09-18 CN CN201510600405.3A patent/CN105221263A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4896499A (en) * | 1978-10-26 | 1990-01-30 | Rice Ivan G | Compression intercooled gas turbine combined cycle |
| US4896499B1 (en) * | 1978-10-26 | 1992-09-15 | G Rice Ivan | |
| CN1165238A (en) * | 1996-04-22 | 1997-11-19 | 亚瑞亚·勃朗勃威力有限公司 | Operation method for combined equipment |
| CN103608567A (en) * | 2011-07-07 | 2014-02-26 | 俄罗斯铁路开放式股份公司 | Gas turbine arrangement for a locomotive |
| WO2015038768A1 (en) * | 2013-09-12 | 2015-03-19 | Florida Turbine Technologies, Inc. | High pressure ratio twin spool industrial gas turbine engine |
| EP2915963A1 (en) * | 2014-03-05 | 2015-09-09 | Siemens Aktiengesellschaft | Cogeneration plant and method to operate a cogeneration plant |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107575310A (en) * | 2017-10-24 | 2018-01-12 | 江苏华强新能源科技有限公司 | A kind of high-efficiency gas turbine air outlet temperature regulating system |
| CN108954374A (en) * | 2018-08-16 | 2018-12-07 | 哈尔滨锅炉厂有限责任公司 | Combined Cycle Heat Recovery Boiler afterburning wind system |
| CN108954374B (en) * | 2018-08-16 | 2023-05-30 | 哈尔滨锅炉厂有限责任公司 | After-combustion air system of combined cycle waste heat boiler |
| CN115324731A (en) * | 2022-08-16 | 2022-11-11 | 星辰萌想科技(北京)有限公司 | Gas turbine |
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