GB676008A - Improvements in or relating to gas turbine plants - Google Patents
Improvements in or relating to gas turbine plantsInfo
- Publication number
- GB676008A GB676008A GB5109/49A GB510949A GB676008A GB 676008 A GB676008 A GB 676008A GB 5109/49 A GB5109/49 A GB 5109/49A GB 510949 A GB510949 A GB 510949A GB 676008 A GB676008 A GB 676008A
- Authority
- GB
- United Kingdom
- Prior art keywords
- water
- turbine
- stages
- compressor
- evaporator
- 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.)
- Expired
Links
Classifications
-
- 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
- F01K21/00—Steam engine plants not otherwise provided for
- F01K21/04—Steam engine plants not otherwise provided for using mixtures of steam and gas; Plants generating or heating steam by bringing water or steam into direct contact with hot gas
- F01K21/047—Steam engine plants not otherwise provided for using mixtures of steam and gas; Plants generating or heating steam by bringing water or steam into direct contact with hot gas having at least one combustion gas turbine
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
676,008. Gas turbine plant, axial flow compressors. SOC. RATEAU, and ANXIONNAZ, R. Feb. 24, 1949 [Oct. 11, 1948; Dec. 10, 1948], Nos. 5109/49 and 5110/49. [A Specification was laid open to inspection under Sect. 91 of the Acts, Aug. 29, 1949.] Classes 110(i) and 110(iii) [Also in Group XII] In a gas turbine plant, in which water is added to the compressed air and is vaporized by the heat of compression in one or more evaporator saturators at least one of the evaporator saturators located after a compressor is provided with means for removing water from its base, and conveying it without heat exchange with the air within the compressor to heating means heated by the turbine exhaust gases and returning it to the evaporator saturator so that it flows from top to bottom in contact with the air delivered by the compressor. The heat extracted from the turbine exhaust for heating the injection water to the evaporator saturators may be controlled by thermostats to prevent condensation of steam in the turbine exhaust. Fig. 2 shows a plant with inter-stage evaporator saturators h 1 , h 2 , h 3 . These may be supplied with unheated water or the water may be heated in exchangers a 3 , a 2 , a 1 . In the former case, a further saturator may be located after the last compressor stage b\ and be supplied with water heated in an exhaust gas heat-exchanger after the preheater a. Thermostats w control valves u in lines which byepass the exchangers so that the exhaust gas temperature shall not fall to the dew point. Water from the evaporated saturator drains s gives up heat in exchanger q to the fresh water from pump n. In Fig. 3 fluid in a closed circuit is heated in an exchanger a 1 and gives up heat in exchangers p 1 , p 2 , P 3 to the injection water for the evaporator saturators h 1 , h 2 , h 3 . The heat taken up in exchangers p 1 , p 2 , is regulated by byepass valves u controlled by thermostats v responsive to the difference between the temperatures of the heated water and the air leaving the evaporator saturator. The heat taken up in exchanger p 3 is regulated by a valve u controlled by a thermostat w responsive to the temperature of the fluid returning to the exchanger a,. The evaporator saturators h 1 , h 2 , h 3 , Fig. 2, comprise an inlet manifold J, feeding a number of tubes J having a cylindrical or other cross-section open at their upper ends but covered by stationary caps k which compel the water to trickle from top to bottom outside the tubes. A separating screen may be set above the tubes to prevent carry over of water particles into the following compressor. In other forms of evaporator saturator described the water is passed directly into the air through atomizing nozzles or trickles on to vertical or sloped plates. In Fig. 5, water is heated in an inter-stage cooler s and in an exhaust heat -exchanger a<SP>1</SP> and is injected into a saturator h located after the compressor delivery. An additional interstage cooler s 1 may be provided In the plant shown in Fig. 6 an inter-cooler l between compressor stages b 1 , b 2 heats the injection water for a saturator h 1 between stages b 2 , b 3 and the water for a saturator h 2 between stages b 3 , b 4 is heated in an exchanger a 1 . Turbine-compressor arrangements.-In Figs. 2 and 3, turbines f 1 , f 2 which drive a generator g are in parallel with turbines f 3 , f 4 . L.P. turbine f 3 drives the H.P. compressor stages b 3 , b 4 and H.P. turbine f 4 drives the L.P. stages b', b<SP>2</SP>. In Fig. 5, the the first and second turbine stages f, drive compressor stages b 1 , b 2 and the last turbine stage f 2 drives a generator g. The turbine stages f, may be in parallel, both exhausting to stage f 2 . In Fig. 6, turbine stages f 1 , f 4 axe in parallel with stages f 2 , f 3 and both pairs exhaust to turbine f 5 . The first and second compressor stages b, b 2 are. driven by the intermediate turbine stages f 3 , f 4 . The third and fourth compressor stages are driven by the H.P. turbine stages f 1 , f 2 . In all the plants, reheating is provided before all following turbine stages. In the plant shown in Fig. 2, starting motors C, C' are provided for the two compressor-turbine sets b 1 , b 2 , f 4 and b 3 , b 4 , f 3 . As in Fig. 3, the motor C<SP>1</SP> may be omitted. The Specification as open to inspection under Sect. 91 of the Acts comprises also a number of modifications of the plants described above. In one of these the feed water to the evaporator saturators is not heated by the turbine exhaust gases whilst in another, the feed water is additionally heated by the compressed air between two of the compressors. A further modification describes a jet propulsion engine in which water is injected between the stages of an axial flow compressor. This subject-matter does not appear in the Specification as accepted.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR286978X | 1948-10-11 | ||
FR101248X | 1948-12-10 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB676008A true GB676008A (en) | 1952-07-23 |
Family
ID=26213377
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB5109/49A Expired GB676008A (en) | 1948-10-11 | 1949-02-24 | Improvements in or relating to gas turbine plants |
Country Status (2)
Country | Link |
---|---|
CH (1) | CH286978A (en) |
GB (1) | GB676008A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2003529701A (en) * | 1999-06-10 | 2003-10-07 | エンハンスド タービン アウトプット ホールディング エル エル シー | Supercharged gas turbine device, supercharged auxiliary device, supercharged gas turbine device operating method, high-pressure fluid transfer duct, and power generation facility |
Families Citing this family (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS5788225A (en) * | 1980-11-25 | 1982-06-02 | Mitsubishi Gas Chem Co Inc | Adding method of water |
DE3275652D1 (en) * | 1981-12-10 | 1987-04-16 | Mitsubishi Gas Chemical Co | Regenerative gas turbine cycle |
US4537023A (en) * | 1981-12-10 | 1985-08-27 | Mitsubishi Gas Chemical Company, Inc. | Regenerative gas turbine cycle |
US4773846A (en) * | 1985-07-30 | 1988-09-27 | Michael Munk | Combustion system and method with fog injection and heat exchange |
US4731990A (en) * | 1985-07-30 | 1988-03-22 | Michael Munk | Internal combustion engine system and method with reduced noxious emissions |
US4702074A (en) * | 1985-07-30 | 1987-10-27 | Michael Munk | Internal combustion engine system with fog injection and heat exchange |
US4731988A (en) * | 1985-07-30 | 1988-03-22 | Michael Munk | Internal combustion engine system and method with reduced noxious emissions |
US5347806A (en) * | 1993-04-23 | 1994-09-20 | Cascaded Advanced Turbine Limited Partnership | Cascaded advanced high efficiency multi-shaft reheat turbine with intercooling and recuperation |
US6012279A (en) * | 1997-06-02 | 2000-01-11 | General Electric Company | Gas turbine engine with water injection |
US6553753B1 (en) | 1998-07-24 | 2003-04-29 | General Electric Company | Control systems and methods for water injection in a turbine engine |
US6470667B1 (en) | 1998-07-24 | 2002-10-29 | General Electric Company | Methods and apparatus for water injection in a turbine engine |
US6598801B1 (en) | 2000-11-17 | 2003-07-29 | General Electric Company | Methods and apparatus for injecting water into gas turbine engines |
-
1949
- 1949-02-24 GB GB5109/49A patent/GB676008A/en not_active Expired
- 1949-07-20 CH CH286978D patent/CH286978A/en unknown
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2003529701A (en) * | 1999-06-10 | 2003-10-07 | エンハンスド タービン アウトプット ホールディング エル エル シー | Supercharged gas turbine device, supercharged auxiliary device, supercharged gas turbine device operating method, high-pressure fluid transfer duct, and power generation facility |
Also Published As
Publication number | Publication date |
---|---|
CH286978A (en) | 1952-11-15 |
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