EP0995038A1 - Gasturbine und verfahren zum betreiben derselben - Google Patents
Gasturbine und verfahren zum betreiben derselbenInfo
- Publication number
- EP0995038A1 EP0995038A1 EP98943724A EP98943724A EP0995038A1 EP 0995038 A1 EP0995038 A1 EP 0995038A1 EP 98943724 A EP98943724 A EP 98943724A EP 98943724 A EP98943724 A EP 98943724A EP 0995038 A1 EP0995038 A1 EP 0995038A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- turbine
- working gas
- gas
- water
- compressor
- 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.)
- Withdrawn
Links
- 238000000034 method Methods 0.000 title claims abstract description 14
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 41
- 238000007906 compression Methods 0.000 claims abstract description 12
- 230000006835 compression Effects 0.000 claims abstract description 11
- 239000012080 ambient air Substances 0.000 claims description 16
- 238000002485 combustion reaction Methods 0.000 claims description 16
- 238000001816 cooling Methods 0.000 claims description 16
- 238000010438 heat treatment Methods 0.000 claims description 10
- 238000000926 separation method Methods 0.000 claims description 5
- 230000002040 relaxant effect Effects 0.000 claims 1
- 239000007789 gas Substances 0.000 description 137
- 239000003570 air Substances 0.000 description 7
- 239000000446 fuel Substances 0.000 description 7
- 238000011144 upstream manufacturing Methods 0.000 description 4
- 238000005457 optimization Methods 0.000 description 3
- 239000007788 liquid Substances 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 238000010276 construction Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 239000003208 petroleum Substances 0.000 description 1
- 231100000719 pollutant Toxicity 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
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/006—Open cycle gas-turbine in which the working fluid is expanded to a pressure below the atmospheric pressure and then compressed to atmospheric 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
- 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
- F02C3/30—Adding water, steam or other fluids for influencing combustion, e.g. to obtain cleaner exhaust gases
-
- 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
- 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
- F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
-
- 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
- F02C7/1435—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid before or between the compressor stages by water injection
Definitions
- the present invention relates to a method for operating a gas turbine and a gas turbine according to the preamble of claims 1 and 5 respectively.
- Gas turbines of the type mentioned above are thermal fluid-flow engines in which the thermal energy is converted from heated working gas into mechanical energy, so-called shaft power.
- a compressor with possibly several compressor stages compresses atmospheric air as working gas and conveys it into one or more combustion chambers, where fuel is sprayed and ignited.
- the high-energy, outflowing working gas is then expanded in a (utility) turbine at least to such an extent that the compressor output to be applied is generated and the compressor is thus driven.
- Working gas or the enthalpy difference can be converted into said shaft power by said turbine or, in the case of multi-shaft construction, by further turbines or turbine stages. Examples of such gas turbines are shown in the prospectus "With energy from gas turbines into the future", edition 03.97 D, and “Gas turbines for mechanical drives", edition 03.96 D.
- the gas turbines work with an open cycle of the working gas. This is to be understood as a demarcation from a closed cycle in which the working gas is recirculated. Accordingly, can be more open
- thermodynamic working process of a conventional gas turbine consists of compression, heat supply and relaxation. This process is also referred to as the Joule process and is explained in more detail, for example, in "Encyclopedia of Natural Science and Technology", Verlag Moderne Industrie, 1981, under the keyword “Turbine (gas turbine)".
- the efficiency is better, the higher the temperature of the heated working gas entering the turbine and the lower the temperature of the ins Free flowing relaxed working gas is.
- the efficiency of a gas turbine depends on the pressure ratio between the upstream and downstream sides of the turbine. A high pressure ratio generally enables high efficiency.
- Gas turbine arrangements are known from DE-A-11 49 573 and US-A-4,414,805 in which a high pressure ratio between the upstream and downstream sides of the turbine is obtained by depressurizing the working gas on the downstream side of the turbine.
- the turbine is driven by a further drive machine
- the external energy for heating the working gas is often provided by burning gaseous or liquid fuels.
- Higher combustion temperatures, i.e. higher heating temperatures of the working gas - usually the combustion air - are conducive to high efficiency, but the working gas temperature is limited by the properties of the materials used, usually around 1100 ° C.
- the relaxed working gas emerging from the turbine at a temperature of, for example, 500 to 600 ° C. for preheating the working gas heated to, for example, 300 ° C.
- a heat exchanger is connected between the compressor and a subsequent combustion system for heating the working gas. Because of the comparatively small temperature difference of only 200 to 300 ° C between the relaxed working gas emerging from the turbine and that from compression heated, yet to be heated working gas, the relaxed working gas leaving the heat exchanger is still at a relatively high temperature and thus still considerable thermal energy which is not used.
- Gas turbines can also be used to drive compressors, for example to maintain sufficient pressure in long gas pipelines.
- the thermal energy of the relaxed working gas emerging from the turbine is not used in these compression processes. Accordingly, the efficiency of these compressors, measured in terms of the total energy used, is relatively low.
- JP-A-59-120721 which forms the starting point, discloses a gas turbine system in which the exhaust gases from an industrial furnace are fed to a turbine at approximately atmospheric pressure.
- the exhaust gases are expanded to a negative pressure in the turbine and then passed through a heat exchanger and a downstream compressor, which compresses the exhaust gases back to atmospheric pressure and allows them to escape to the outside.
- the turbine drives the compressor and a blower, which supplies ambient air to the industrial furnace, the ambient air in the heat exchanger being preheated by the exhaust gases expanded to negative pressure.
- the present invention is based on the object of specifying a method for operating a gas turbine and a gas turbine which enable the realization of an efficiency which is higher than that of the prior art.
- An essential aspect of the present invention is to generate a pressure drop on the downstream side of the turbine instead of increasing the inlet pressure of the working gas. This makes it possible to at least reduce the compression and the associated increase in temperature of the working gas before heating and subsequent introduction into the turbine, or to eliminate it entirely. As a result, the temperature difference between the working gas emerging from the turbine and expanded to negative pressure and the working gas to be preheated before the heating is increased. The increased temperature difference enables better feedback of thermal energy during heat exchange and thus a significantly higher efficiency of the gas turbine.
- a very effective heat feedback is preferably achieved in that the heat exchanger is designed as a counterflow heat exchanger, in particular in the form of a recuperator.
- a basic idea of the present invention is to separate water from the working gas which has been expanded to negative pressure before compression. Since a significant proportion of the working gas, especially when burning fuel in ambient air, consists of water, the volume and mass flow of the working gas still to be compressed and thus the power required for this can be reduced significantly.
- the compression of the separated water to ambient pressure or a pressure above it is comparatively less energy-intensive and is more than compensated for by the reduction in the compressor output required, so that overall an optimization of the efficiency is made possible.
- a further optimization of the efficiency is made possible by the fact that separated water is at least partially reintroduced into the working gas before it is expanded in the turbine, in particular injected. In this way, the mass flow of the working gas through the turbine is increased, so that more thermal energy is supplied to the turbine at the same working gas temperature. In this way, the efficiency can be further optimized.
- separated water can be injected into the heat exchanger, which is preferably designed as a recuperator, for manipulating the heat capacity of the heat-exchanging gases, thereby making it possible to optimize the heat exchange between the working gas which is still to be heated and the working gas which has been depressurized.
- the pollutant content, in particular the NO x content, in the exhaust gas can be reduced.
- the efficiency can be increased by increasing the temperature of the working gas that can be supplied to the turbine. This is made possible by cooling blades of the turbine, at least blades arranged on the inlet side. This blade cooling can be achieved by separated water which is supplied to blades provided with corresponding channels.
- the compressor works as a suction pump on the outflow side in order to maintain the negative pressure on the outflow side of the turbine. Compression of the working gas to be preheated or the ambient air drawn in can be completely eliminated or at least reduced.
- ambient air is used as the working gas and a fuel, in particular natural gas or petroleum, is burned in the working gas for heating. So with minimal constructive
- Efficient heating of the working gas can be achieved. Achieving a high degree of efficiency is further supported by the fact that the working gas expanded to negative pressure after the heat exchange, in which it is recooled, for example, from 700 ° C. to 75 ° C., is cooled further before compression, in particular when or for separating water is to minimize the required compressor power and thus the power to be applied by the turbine, taking into account the power required for further cooling.
- Underpressure in the sense of the present invention can generally also be a pressure above ambient or atmospheric pressure, provided that it is below the inlet pressure of the working gas into the open circuit or into the gas turbine.
- a very good efficiency can be achieved in that a negative pressure of less than 50 kPa, preferably essentially 30 kPa, can be generated and that the heat exchanger, the working gas to be preheated, preferably ambient air, can be supplied essentially at ambient temperature, in particular without prior compression .
- Fig. 1 shows a schematic structure of a proposed gas turbine
- Fig. 2 is a greatly simplified enlargement of a turbine with blade cooling by ambient air.
- the proposed gas turbine 1 shown in FIG. 1 comprises, corresponding to known gas turbines, a compressor 2, a combustion system 3 for heating a working gas, a (utility) turbine 4 which can be driven with the heated working gas, and a heat exchanger 5 which preheats the gas from the Combustion system 3 to be heated working gas with the aid of the still relatively hot working gas flowing out of the turbine 4.
- the compressor 2 is designed, for example, as a paddle wheel compressor and can be driven by the turbine 4 via a common shaft 6.
- the working gas formed by the ambient air sucked in is not or only at least comparatively compressed, for example to 200 kPa, before preheating in the heat exchanger 5. Accordingly, the working gas can enter the heat exchanger 5 via an inlet 7 at a temperature corresponding at least substantially to the ambient temperature and preferably at approximately ambient pressure. The working gas is preheated in the heat exchanger 5 and is fed to the subsequent combustion system 3 via a line 8
- the combustion system 3 for example, which burns gaseous or liquid fuels, then heats the working gas to, for example, approximately 1100 ° C.
- the pressure of the working gas is essentially not increased. It therefore still corresponds approximately to the ambient pressure or the inlet pressure of the working gas into the open circuit at inlet 7.
- the heated working gas is then fed to the turbine 4 via a line 9.
- the turbine 4 the thermal energy of the working gas is partially converted into mechanical energy, which on the one hand is transmitted to the compressor 2 via the shaft 6 and on the other hand is made available as so-called shaft power.
- the heated working gas is expanded to a vacuum which is present on the outflow side of the turbine 4 and is preferably less than 50 kPa and in particular 30 kPa or less, with the pressure emerging from the turbine 4 or via a line 10 to the heat exchanger 5 outflowing working gas in turbine 4, for example, has cooled to about 700 ° C.
- the optimal vacuum for maximum efficiency depends on the technologically achievable or realized turbine inlet temperature.
- the working gas expanded to negative pressure gives off heat energy in the heat exchanger 5 to the working gas still to be heated in the combustion system 3.
- An effective heat exchange is preferably achieved in that the heat exchanger 5 is designed as a recuperator operating in countercurrent. Due to the high temperature difference of approximately 700 ° C between the working gas relaxed to negative pressure and the working gas to be preheated and then heated, a relatively large amount of thermal energy can be transferred.
- the working gas expanded to negative pressure is cooled by the heat exchanger 5, for example, to about 75 ° C. and then passed on via lines 11 and 12 to the compressor 2 driven by the turbine 4.
- the compressor 2 then compresses the working gas expanded to negative pressure back to ambient pressure and allows it to escape to the outside via an outlet 13.
- the gas turbine 1 thus has an open circuit for the working gas.
- the compressor 2 does not serve to increase the pressure of the working gas above the ambient pressure, but rather to maintain the negative pressure on the outflow side of the turbine 4.
- the compressor 2 operates, so to speak, as a vacuum pump, which is arranged at the end of the flow path of the working gas. Calculations have shown that the gas turbine 1 according to the illustrated embodiment can achieve an efficiency of 50% or more (mechanical energy or shaft power output in relation to the fuel energy used).
- an intermediate cooler 14 is preferably arranged in the flow path of the working gas expanded to negative pressure between the heat exchanger 5 and the compressor 2, which serves to further reduce the temperature of the working gas which has been pre-cooled by the heat exchanger 5 and expanded to negative pressure before compression .
- a water separator 15 is connected between the lines 11 and 12, that is to say upstream of the compressor 2, in order to separate water present in the working gas which has been released to negative pressure before the working gas is compressed. This significantly reduces the required compressor output.
- the intercooler 14 and the water separator 15 can optionally also be designed as a structural unit, so that the dew point of the working gas expanded to negative pressure in the intercooler 14 is undershot and the water which has condensed out is immediately removed.
- a pump 16 is connected to the water separator 15, which at least brings the separated water back to ambient pressure, so that the separated water can be released to the environment, for example via an outlet 17.
- the separated water is preferably partly returned to the working gas before flowing through the turbine 4.
- separated water is introduced, for example, into the combustion system 3 or into a combustion chamber thereof.
- the NO x portion of the combustion air can be reduced and, on the other hand, the mass flow of the working gas flowing through the turbine 4 can be increased.
- the efficiency of the gas turbine 1 can be increased further by increasing the mass flow.
- the required power of the pump is 16 Bring separated water back to ambient pressure or a pressure above it or compress it negligibly low.
- separated water can also be introduced into the working gas before or after flowing through the combustion system 3, for example in the area of the line 8 or 9.
- separated water can be introduced, in particular injected, into the flow path of the working gas through the heat exchanger 5 from the inlet 7 to the line 8. In this way, on the one hand, an increase in the mass flow of the working gas supplied to the turbine 4 can be brought about and, on the other hand, an optimization of the heat capacity or the temperature dependence of the heat capacity of the working gas flowing through the heat exchanger 5 and then still to be heated can be achieved to maximize the heat exchange taking place in the heat exchanger 5 .
- water separated from the water separator 15 can be used to cool the blades of the turbine 4, so that the permissible turbine inlet temperature, i. H. the temperature of the working gas entering the turbine 4 can be increased, whereby an improvement in efficiency can also be achieved.
- blade cooling is provided not by separated water but by ambient air.
- the greatly simplified partial enlargement of the turbine 4 according to FIG. 2 illustrates such a blade cooling.
- the turbine 4 has a number of rows of non-rotating guide vanes 19 arranged one behind the other and a number of rows one behind the other, some lying between them, of rotor blades 20 carried by the rotatable shaft 6.
- heated working gas enters the turbine 4 according to arrows 21 and exits from it according to arrows 22.
- the guide vanes 19 and rotor blades 20 are the two rows closest to the inlet side and the shaft 6 hollow at least in the area of these blades 20, so that ambient air flows into the hollow guide vanes 19 on the one hand according to arrows 23 and into the hollow guide vanes 20 on the other hand according to arrows 24 and in each case through outlet openings arranged in particular in the outflow side into the turbine interior, i.e. into the working gas according to arrows 25 can flow out.
- the optional blade cooling is made possible by suction of air, in particular by the expansion of the working gas in the turbine 4 to negative pressure.
- this blade cooling can be implemented independently of the separation of water from the working gas expanded to negative pressure, that is to say even if no water separator 15 is provided, in order to make it possible to increase the efficiency of the gas turbine system or gas turbine 1 by increasing the turbine inlet temperature.
- the inlet 7 of the heat exchanger 5 for the working gas to be preheated is not preceded by a compressor for the working gas.
- a device for supplying working gas upstream of the inlet 7, which is driven, for example, by the turbine 4 and increases the inlet pressure of the working gas if the temperature of the working gas is relatively small.
- the gas turbine 1 is single-shaft.
- the gas turbine 1 can of course also be designed with multiple shafts, in particular with two shafts.
- the multi-shaft design of the gas turbine 1 is particularly suitable for the use of the gas turbine 1 as a mechanical drive, for example for driving a compressor for pipeline compressor stations.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
Description
Claims
Applications Claiming Priority (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19730067 | 1997-07-14 | ||
DE19730067 | 1997-07-14 | ||
DE19732268A DE19732268C2 (de) | 1997-07-14 | 1997-07-26 | Verfahren und Vorrichtung zum Verdichten eines Arbeitsgases |
DE19732268 | 1997-07-26 | ||
PCT/EP1998/003807 WO1999004170A1 (de) | 1997-07-14 | 1998-06-22 | Gasturbine und verfahren zum betreiben derselben |
Publications (1)
Publication Number | Publication Date |
---|---|
EP0995038A1 true EP0995038A1 (de) | 2000-04-26 |
Family
ID=26038267
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP98943724A Withdrawn EP0995038A1 (de) | 1997-07-14 | 1998-06-22 | Gasturbine und verfahren zum betreiben derselben |
Country Status (2)
Country | Link |
---|---|
EP (1) | EP0995038A1 (de) |
WO (2) | WO1999004169A1 (de) |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2351776A (en) * | 1999-07-03 | 2001-01-10 | Rolls Royce Plc | A gas turbine engine |
CN113758968B (zh) * | 2021-09-30 | 2022-08-05 | 西安交通大学 | 一种用于测量透平动叶叶顶换热系数的实验***和稳态实验方法 |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
BE624459A (de) * | ||||
FR1166419A (fr) * | 1955-07-08 | 1958-11-12 | Procédé et moyens de mise en oeuvre pour tirer de l'énergie mécanique de la chaleur sensible d'une masse gazeuse chaude, sensiblement à la pression atmosphérique ambiante, et application aux turbines à gaz | |
GB905663A (en) | 1959-06-01 | 1962-09-12 | Havilland Engine Co Ltd | Power plant including a gas turbine |
US4414805A (en) | 1981-11-27 | 1983-11-15 | General Motors Corporation | Hybrid gas turbine engine and flywheel propulsion system |
JPS59120721A (ja) | 1982-12-27 | 1984-07-12 | Osaka Gas Co Ltd | 排熱回収装置 |
DE3345027A1 (de) * | 1983-12-13 | 1985-06-13 | Linde Ag, 6200 Wiesbaden | Verfahren zur aufbereitung von synthesegasen |
GB2216191B (en) * | 1988-03-31 | 1992-08-12 | Aisin Seiki | Gas turbine cogeneration apparatus for the production of domestic heat and power |
EP0596143A4 (de) * | 1992-05-25 | 1994-12-07 | Aktsionernoe Obschestvo Kryoko | Gas-verteileranlage mit energierückgewinnung. |
RU2095634C1 (ru) * | 1995-12-28 | 1997-11-10 | Акционерное общество Научно-исследовательский и конструкторский институт центробежных и роторных компрессоров | Комбинированный газоперекачивающий агрегат |
-
1998
- 1998-06-20 WO PCT/EP1998/003780 patent/WO1999004169A1/de active Application Filing
- 1998-06-22 WO PCT/EP1998/003807 patent/WO1999004170A1/de not_active Application Discontinuation
- 1998-06-22 EP EP98943724A patent/EP0995038A1/de not_active Withdrawn
Non-Patent Citations (1)
Title |
---|
See references of WO9904170A1 * |
Also Published As
Publication number | Publication date |
---|---|
WO1999004169A1 (de) | 1999-01-28 |
WO1999004170A1 (de) | 1999-01-28 |
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