GB2236145A - Gas turbine engine steam cooling - Google Patents

Gas turbine engine steam cooling Download PDF

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Publication number
GB2236145A
GB2236145A GB9016558A GB9016558A GB2236145A GB 2236145 A GB2236145 A GB 2236145A GB 9016558 A GB9016558 A GB 9016558A GB 9016558 A GB9016558 A GB 9016558A GB 2236145 A GB2236145 A GB 2236145A
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United Kingdom
Prior art keywords
turbine
steam
passageway
combustor
powerplant
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GB9016558A
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GB9016558D0 (en
Inventor
William Ronald Hines
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General Electric Co
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General Electric Co
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Publication of GB9016558D0 publication Critical patent/GB9016558D0/en
Publication of GB2236145A publication Critical patent/GB2236145A/en
Withdrawn legal-status Critical Current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
    • 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
    • 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
    • F01K23/00—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids
    • F01K23/02—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled
    • F01K23/06—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle
    • F01K23/10—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle with exhaust fluid of one cycle heating the fluid in another cycle
    • F01K23/106—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle with exhaust fluid of one cycle heating the fluid in another cycle with water evaporated or preheated at different pressures in exhaust boiler
    • 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
    • F02C6/003—Gas-turbine plants with heaters between turbine stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium
    • F05D2260/2322—Heat transfer, e.g. cooling characterized by the cooling medium steam
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • F05D2260/601—Fluid transfer using an ejector or a jet pump
    • 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
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Separation By Low-Temperature Treatments (AREA)
  • Gas Separation By Absorption (AREA)

Abstract

In a powerplant comprising in flow sequence a compressor 20, a combustor 22 and a turbine 30a, 30b having a plurality of stages 34. A plurality of turbine stage vanes 36 are positioned prior to the turbine rotor stages 34 and the vanes 36 have passageways 38 therethrough. Steam from a supply means 40 is supplied via a passageway 38 of a least one of the turbine stage vanes 36 to a steam injector 44 for injecting steam into or upstream of the combustor 22. Air is supplied via a valve 48 to the passageways 38 and during the start up period provides the system cooling when steam is not available. Two combustors (222a, 222b), Fig 2, may be provided, each having its own steam (210, 212) and air supplies. A supplementary burner (310), Fig 3 and high pressure boiler (314), low pressure boiler (316) and very low pressure boiler (318) may be provided downstream of the turbine section (330b). <IMAGE>

Description

GAS TURBINE ENGINE STEAM COOLING The invention relates to powerplants and, msre particularly, to turbine vane cooling in powerplants.
Efficiency of powerplants and, in particular, gas turbine engines can be improved by operating at high temperatures. However, since temperature limitations exist in metal alloys used to form the engine, numerous cooling techniques have been developed to allow increases in operating temperatures. In particular, gas turbine engines typically have a compressor, a combustor, and a turbine wherein the turbine has a plurality of stages and turbine stage vanes are typically positioned prior to each stage of the turbine. During engine operation the turbine vanes are subjected to intense temperatures and therefore these vanes require advanced cooling techniques. Typically, in order to cool these vanes, air will be bled off from the compressor and will be injected into passageways in the vanes.The compressed air then exits the vane into the flowpath of the engine through openings which extend from the passageway to the surface of the vane. Unfortunately, air provides limited cooling ability due to its physical characteristics. Further, using air from the compressor for cooling reduces cycle efficiency as this air bypasses both the combustor and at least a portion of the turbine stages until it is reinjected into the flowpath of the engine. Other proposed vane cooling techniques utilize steam which enters vane passageways and then exits into the engine flowpath through openings in the vanes. However, these systems also reduce efficiency by having steam bypass some turbine stages of the engine system.
Other cooling systems do not address the particular difficulties associated with vane cooling.
For example, some systems inject water into a turbine for cooling and then as this water turns to steam, the steam is injected into the combustor. However, these systems require major redesign of current cooling flow systems to allow the use of water. Centrifugal forces may also inhibit proper cooling flows and additional heating systems or flow controls may be necessary to insure that excess water is not injected into the combustor which may hinder combustion and may damage engine components. Other cooling systems have been primarily designed for controlling portions of the engine, such as tip clearances to increase efficiency. Systems have been proposed which utilize large amounts of compressed air to cool an engine shroud and then the air is reintroduced into a combustor of the engine.Unfortunately, these systems reduce engine efficiency since pressure and energy losses occur in the circulating and cooling air and these systems also have not been designed for the particular problems posed by vane cooling. Further, any air cooling system which introduces the heated air back into a main combustor must have a sink, which is normally inside the dome and skirts of the combustor, wherein the discharge air pressure of the high pressure compressor has been subsequently reduced by necessity to a lower total pressure than that for the re-entering cooling air.
Therefore, it would be desirable to have a powerplant having an improved vane cooling system.
According to the invention in one aspect thereof, a powerplant comprises a ~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ compressor for producing a downstream flow, a combustor downstream of the compressor, and a turbine, having a plurality of rotor stages, positioned downstream of the combustor. A plurality. of turbine stage vanes are positioned prior to the turbine rotor stages and the vanes have a passageway therein. A means for supplying steam is positioned downstream of the turbine wherein an output of the means for supplying steam is coupled to an input of a passageway of a least one of the turbine stage vanes. An injection means is coupled to an inlet of a combustor and the output of the vane passageway is coupled to the injection means.
The invention also includes a method for cooling a gas turbine engine having a compressor for producing a downstream flow, a combustor downstream of the compressor, and a turbine downstream of the combustor wherein the turbine has a first turbine stage vane having a passageway therein. The steps comprise introducing steam into an inlet of the passageway and introducing steam which has exited the passageway into a combustor of the engine, upstream of the turbine.
In the accompanying drawings: FIGURE 1 is a schematic diagram of one embodiment of the invention.
FIGURES 2 and 3 are schematic diagrams of other embodiments of the invention.
FIGURE 4 is a schematic diagram of an ejector-type mixer.
In Fig. 1, a powerplant 10 of embodying the invention comprises a compressor 20, such as a high pressure compressor and a low pressure compressor, for producing a downstream flow, a combustor 22 is positioned downstream of the compressor 20, a turbine 30 such as a high pressure turbine 30a and a low pressure turbine 30b is positioned downstream of the combustor 22. Typically, the high pressure turbine 30a is drivingly connected to the high pressure compressor and the low pressure turbine 30b is drivingly connected to the low pressure compressor.
The turbine 30 typically has a plurality of turbine rotor stages 34. Turbine vanes 36 are typically positioned prior to each of the turbine rotor stages 34 and each of the turbine vanes 36 typically has a cooling passageway 38 therein. A means for supplying steam 40, such as a high pressure boiler is positioned downstream of the turbine 30 and the output of the means for supplying steam 40 is coupled to a steam valve 42 and the output of the steam valve 42 is coupled to an input of the passageway 38 of at least one turbine vane 36 and the output of the turbine vane passageway 38 is coupled to an injection means 44 which is coupled to an inlet of the combustor 22.
Preferably, a means for obtaining cooling air 46, which is typically at a compressor outlet such as a bleed valve, is coupled to an air valve 48 and the output of the air valve is coupled to the input of the passageways 38 and the steam valve 42.
The compressor 20, combustor 22 and turbine 30 may be of any type used for powerplants. Preferably, these components are derived from those utilized in aircraft engines and the compressor 20 will often have a first compressor or booster (not shown) which is drivingly connected to the low pressure turbine 30b and a second compressor is drivingly connected to the high pressure turbine 30a. It should be understood that the invention is applicable to engines having single or multiple compressors and turbines.
Typically, the turbine will also comprise a free or aerodynamically coupled power turbine downstream of the low pressure turbine and from which power may be extracted by attaching various devices such as a propeller or a generator. The powerplant 10 may have single or multiple combustors or burners which are positioned within the flow path of the powerplant 10 upstream of the means for supplying steam 40, as depicted in Fig. 2. Typically, if a reheat combustor is used the reheat combustor will be positioned between the low pressure turbine 30b )and the power turbine.
The turbine vanes 36 of Fig. 1 are typically also of an aircraft derivative type. However, as compared to aircraft air cooled vanes, the turbine vanes typically have a reduced amount of holes which extend from the passageway to the surface thereby reducing the amount of cooling fluid which may escape into the downstream flow. While in certain applications these holes may be entirely eliminated, typically holes are formed on the inner diameter of the vane such that cooling fluid may escape and cool a cavity 50 which exists below or near the inner diameter of the vane. One such vane structure is described by D. M. Kercher in U.S. Patent 3,533,711 entitled "Cooled Vane Structure for High Temperature Turbines." However, other vane structures having cooling passages therein are equally applicable to the present invention.
The means for supplying steam 40 may be an external source, but is preferably a system which recovers heat which exits the engine such as a high pressure boiler. The means for supplying steam 40 is preferably designed to provide steam at about and typically just above saturation temperature. It should be understood that additional boilers of varying pressure or other means for supplying steam are equally applicable to the present invention.
Preferably, multiple paths for vane cooling are formed by coupling the output of the boiler to passageways 38 in a first set of vanes, such as vanes in the high pressure turbine 30a, and the boiler is also coupled separately to passageways in a second set of vanes in the low pressure turbine 30b. The output of the passageways are typically coupled to passageways in vanes upstream to another set of vanes and then into the injection means 44. It should be understood that typically it is desirable to produce large quantities of steam for injection into the engine. Additionally, as the pressure of water supplied to the boilers is decreased the amount of steam the boilers will produce increases. Therefore, it is desirable to have the boilers supply as low of pressure of steam as possible to maximize steam output.By providing multiple paths for vane cooling, as compared to a single cooling path, increases in performance of the powerplant may be obtained as each path has a reduced amount of pressure losses prior to the steam being injected into the engine. Further, by providing multiple cooling paths the effectiveness of the cooling will increase since the steam being supplied to subsequent passageways 38 will be of a lower temperature. For efficiency enhancement the energy of the steam exiting the passageways for injection into the engine should be of a higher energy than the cooling air which the steam is replacing. Typically, cooling air is obtained from compressor discharge and therefore the cooling steam exiting the passageways and being injected in the engine should be of a temperature which is higher than the compressor discharge.
The means for injecting steam 44 may be any injection means for injecting steam into an inlet of a combustor of the powerplant 10 and is typically a nozzle positioned either in or around the combustor 22. For example, the nozzle may be a dual flow nozzle for injecting both fuel and steam into the combustor.
Alternatively, the steam may enter through ports such as ports typically used for aircraft bleed ports. It should be understood that the means for injecting steam may be positioned upstream of the combustor such.
that the steam flows downstream into the combustor 22.
In operation, air enters through the compressor 20 and a portion of the compressed air enters the combustor 22. The heated air and remaining compressed air which typically surrounds the combustor 22 for cooling then passes through the turbine 30, thereby driving the compressor 20. Simultaneously, steam from the means for supplying steam 40 is introduced into at least one vane passageway 38. The steam cools the vane 36 and is then introduced into the engine into an inlet of the combustor, such that the steam enters the combustor 22. It should be understood that typically in order to minimize piping, steam after exiting a passageway 38 is then introduced into passageways 38 of other vanes 36 prior to the steam being injected in the combustor 22. The steam and air valves1 42 and 46 respectively, control the amount of steam and air entering the passageways 38.
Therefore during initial engine start-up when steam is not available, air may provide system cooling and the system may continue to operate at or near normal operating temperatures. Typically, for engine starting, cooling. air will be circulated through the passageways for about 20 minutes until the boilers are brought on-line. Further, the valves provide a means for obtaining a mixture of steam and air which may be desirable to control the amount of steam supplied and to also control temperature gradients which may affect the life of parts. This powerplant system incorporating steam cooling in vanes provides a number of benefits over previous techniques. The present system utilizes the superior cooling characteristics of steam as compared to air. Further, unlike other cooling substances, steam can be used in passages previously designed for air cooling.Thus, current powerplant designs may incorporate the present invention without major modifications and redesign of the powerplants and their cooling systems and the amount of air required to be diverted for cooling purposes may be reduced. Further, particularly during engine shutdown, it may be desirable to eliminate steam within the system and this system allows the steam to be purged with air thereby avoiding any undesirable condensation which may form inside the vanes. Additionally, the present invention provides improvements in overall efficiency by introducing steam into a combustor of the engine having a higher superheat, resulting from the steam cooling of vanes.
Cycle efficiency improvements are obtained by recuperating heat expended by the engine downstream of forward turbine rotor stages, increasing the heat and mass supplied to the engine forward of the turbine rotor stages, and reducing the amount of cooling air fluid which bypasses the turbine stages through the turbine vanes.
As shown in Fig. 2, another embodiment of a powerplant 200 of the present invention is depicted, wherein like numerals correspond to like elements of Fig. 1. The powerplant 200 comprises a first combustor 222a positioned downstream of the compressor 20 and a second combustor 222b positioned downstream of the high and low pressure turbines 30a and 30b respectively. Downstream of the second combustor 222b is a power turbine 30c and the means for producing steam 40 is downstream of the power turbine 30c. The means for producing steam 40 comprises a first boiler 210 and a second boiler 212 which has a steam output pressure which is typically less than the first boiler 210. The first boiler 210 is coupled through a first steam valve 242a through a first set of vane passageways 238a to an inlet of the first combustor 222a.The second boiler 212 is typically coupled through a second steam valve 242b to a second set of vane passageways 238b and the output of the second set of passageways 238b is coupled to the second combustor 222b. The first steam valve 242a and the first set of passageways 238a are coupled to a first air valve 248a which is coupled to an outlet 246 of the compressor 20 and the second steam valve 242b and second set of passageways 238b are coupled to a second air valve 248b which is coupled to an outlet of the compressor 20. In operation steam is produced by the first and second boilers, 210 and 212 respectively, and the output of the first boiler passes through the first set of passageways 238a into the first combustor 222a. The output of the second boiler 212 passes through the second set of passageways 238b into the second combustor 222b. The first and second air valves, 248a and 248b respectively provide a means for mixing steam with air, purging the passageways of steam and allows the operation of the system with air cooling when steam is not available. When air and steam are mixed it may be desirable to use the steam as an ejector type mixer as depicted in Fig. 4. In Fig. 4 an ejector type mixer 400 comprises air piping 410 for carrying cooling air and a steam nozzle 420 which is disposed in the piping 410 such that the steam exit 422 of the nozzle 420 is spaced apart from sidewalls of the piping 410. In operation, the steam which exits the nozzle 420 is of a higher total pressure than the air in the piping 410 and as the steam enters the piping 410 an air and steam mixture is formed having a substantially uniform total pressure for entering the passageways of the vanes to be cooled.Returning to Fig. 2, in this powerplant 200 one boiler having a lower output pressure may be utilized to provide the cooling for the second set of passageways 238b and this steam may be injected into the second combustor 222b. Typically, for maximum efficiency enhancement it may be desirable to input the steam into the highest temperature combustor, which is typically the first combustor 222a.
As depicted in Fig. 3 wherein like numerals correspond to like elements of Fig. 1 the present invention may be also incorporated in a powerplant 300 comprising a first turbine section 330a and a second turbine section 330 wherein the second turbine section 330b has second turbine section vanes 336 having a second set of vane passageways 320 therein. A supplementary burner 310 is positioned downstream of the second turbine section 330b. Typically, flow straighteners 312 are positioned between the supplementary burner 310 and the low pressure turbine 330b. A high pressure boiler 314 is positioned downstream and adjacent the supplementary burner 310, a low pressure boiler 316 is positioned downstream and adjacent the high pressure boiler 314 and a very low pressure boiler 318 is positioned downstream and adjacent the low pressure boiler 316.The output of the high and low pressure boilers, 314 and 316, are typically coupled to the engine such as for steam cooling and NOx control as in Fig. 2 and the output of the very low pressure boiler 318 is coupled to the second set of vane passageways 320 which passes through the vanes typically through piping into a engine cavity 322 below the vanes and the steam in the engine cavity 322 then flows past the remainder of the engine and reenters the engine flowpath upstream of the supplementary burner 310. The cooling steam in the vane may exit the trailing edge of the vane and then pass into the flowpath upstream of the supplementary burner 310. The first turbine section 330a is typically a high pressure turbine and the second turbine section 330b is typically either a low pressure turbine or a preferably a power turbine. In this system very low pressure steam mass flow may replace higher pressure compressor cooling air flows for cooling latter stages of the low pressure turbine vanes and cavities and therefore the higher pressure compressor air may then now pass through all the upstream turbine stages to improve performance.
It should be understood that the present invention is applicable to a variety of configurations ranging from basic systems having a single compressor, combustor, and turbine to more complex systems having multiple compressors, turbines and combustors and in which the combustors in which the steam is eventually injected into may be positioned at any location in the powerplant upstream of the boilers. It is therefore, to be understood that the appended claims are intended to cover all such modifications and changes as fall within the scope of the invention.

Claims (18)

1. A powerplant comprising: a compressor for producing a downstream flow; a combustor downstream of the compressor; a turbine having a plurality of stages, said turbine positioned downstream of said combustor; a plurality of turbine stage vanes having a passageway therein wherein said vanes are positioned prior to said turbine stages; a means for supplying steam positioned downstream of said turbine wherein an output of said means for supplying steam is coupled to an input of a passageway of a least one of said turbine stage vanes; and an injection means coupled to said combustor wherein the output of said passageway is coupled to said injection means.
2. The powerplant of claim 1 further comprising a means for supplying air wherein said means for supplying air is coupled to said turbine stage vane which is coupled to the output of said means for supplying steam.
3. The powerplant of claim 2 wherein said means for supplying steam is coupled to a valve prior to the input of said turbine stage vane.
4. The powerplant of claim 2 wherein said means for supplying air is coupled to a valve prior to the input of said turbine stage vane.
5. The powerplant of claim 2 further comprising a steam ejector mixer wherein said means for supplying air and said means for supplying steam is coupled to said mixer and the output of said mixer is coupled to said input of a passageway of at least one turbine stage vane.
6. The powerplant of claim 1 wherein said output of said passageway is coupled to a passageway of a second turbine stage vane prior to said injection means.
7. The powerplant of claim 6 wherein said second turbine stage is downstream of said turbine stage vane.
8. The powerplant of claim 1 wherein an output of said means for supplying steam is coupled to a passageway of a first turbine vane and a second output of said means for supplying steam is coupled to a passageway of a second turbine vane.
9. The powerplant of claim 1 wherein said injection means is positioned upstream of said turbine.
10. The powerplant of claim 1 wherein said turbine comprises a high pressure turbine and a low pressure turbine positioned downstream of said high pressure turbine and a second combustor is positioned between the low and high pressure turbines.
11. The powerplant of claim 1 wherein said turbine comprises a high pressure turbine, a low pressure turbine positioned downstream of said high pressure turbine, and a power turbine positioned downstream of said low pressure turbine, and a second combustor is positioned between the low pressure and the power turbines.
12. The powerplant of claim 1 further comprising a second combustor which is positioned between said turbine and said means for supplying steam.
13. The powerplant of claim 1 wherein said turbine comprises a first turbine section and a second turbine section having second turbine section vanes and said second turbine section is positioned downstream of said first turbine section, and a second combustor is positioned downstream of said power turbine and wherein said means for supplying steam further comprises a means for producing low pressure steam which is coupled to input of a passageway of at least one second turbine section vane and said steam exiting the second turbine section vane passageway reenters the flowpath upstream of said second combustor
14.A method for cooling a gas turbine engine having a compressor for producing a downstream flow, a combustor downstream of the compressor, a turbine downstream of the combustor wherein said turbine has a first turbine stage vane having a passageway therein comprising the steps of: introducing steam into an inlet of said passageway; and introducing steam which has exited said passageway into a combustor of said engine.
15. The method of claim 14 wherein said turbine has a secopd turbine stage vane having a passageway therein further comprising the step of introducing said steam which has exited said passageway of said first vane into said passageway of said second vane prior to the step of introducing said steam into the engine.
16. The method of claim 14 further comprising the step of introducing air into said inlet of said passageway.
17. The method of claim 14 further comprising the steps of: simultaneously introducing air and steam into an inlet of said passageway; and introducing said air and steam which has exited said passageway into a combustor of said engine.
18. A powerplant substantially as hereinbefore described with reference to Figure 1, 2 or 3 of the accompanying drawings.
GB9016558A 1989-07-28 1990-07-27 Gas turbine engine steam cooling Withdrawn GB2236145A (en)

Applications Claiming Priority (1)

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US38606989A 1989-07-28 1989-07-28

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GB2236145A true GB2236145A (en) 1991-03-27

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IT (1) IT1243682B (en)
SE (1) SE9002512L (en)

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US5320483A (en) * 1992-12-30 1994-06-14 General Electric Company Steam and air cooling for stator stage of a turbine
US5340274A (en) * 1991-11-19 1994-08-23 General Electric Company Integrated steam/air cooling system for gas turbines
EP0615061A1 (en) * 1993-03-11 1994-09-14 Hitachi, Ltd. Combined cycle power plant and method of operating it
EP0681099A2 (en) * 1994-05-02 1995-11-08 ABB Management AG Gasturbine power station
EP0684369A1 (en) * 1994-04-28 1995-11-29 Westinghouse Electric Corporation Steam cooling of gas turbine with backup air cooling
WO1996018810A1 (en) * 1994-12-12 1996-06-20 Westinghouse Electric Corporation Recuperative steam cooled gas turbine
US5536143A (en) * 1995-03-31 1996-07-16 General Electric Co. Closed circuit steam cooled bucket
EP0795685A1 (en) * 1996-03-14 1997-09-17 Asea Brown Boveri Ag Multi-staged gas-turbine with steam cooling and feeding into the combustor
EP0851104A1 (en) * 1996-12-27 1998-07-01 Asea Brown Boveri AG Gas turbine with heat recovery steam generator for cooling the combustion chamber, then injecting downstream of the combustion zone
WO1998049438A1 (en) * 1997-04-30 1998-11-05 Siemens Westinghouse Power Corporation Power plant with partial oxidation and sequential combustion
WO1998051914A1 (en) * 1997-05-13 1998-11-19 Siemens Westinghouse Power Corporation Partial oxidation powerplant with sequential combustion
US5941687A (en) * 1996-11-12 1999-08-24 Rolls-Royce Plc Gas turbine engine turbine system
EP0995891A2 (en) 1998-10-20 2000-04-26 Asea Brown Boveri AG Turbomachine and method for its operation
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SE9002512L (en) 1991-01-29
GB9016558D0 (en) 1990-09-12
JPH0396628A (en) 1991-04-22
IT1243682B (en) 1994-06-21
IT9021020A0 (en) 1990-07-23
SE9002512D0 (en) 1990-07-26
IT9021020A1 (en) 1992-01-23

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