WO1995014854A1 - Gasarmatur - Google Patents
Gasarmatur Download PDFInfo
- Publication number
- WO1995014854A1 WO1995014854A1 PCT/DE1994/001312 DE9401312W WO9514854A1 WO 1995014854 A1 WO1995014854 A1 WO 1995014854A1 DE 9401312 W DE9401312 W DE 9401312W WO 9514854 A1 WO9514854 A1 WO 9514854A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- common wall
- slots
- compressor
- gas valve
- slide
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/26—Controlling the air flow
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
-
- 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
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
- F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
Definitions
- the invention relates to a gas fitting for an arrangement comprising a gas turbine, a compressor for combustion air and a combustion chamber, a compressor outlet and a turbine inlet having a common wall.
- an air duct for the compressed combustion air has an annular cross section and u-closes a duct for hot air flowing to the turbine
- Propellant In the air duct, in the vicinity of the compressor, there is a valve chamber with a plurality of valve openings arranged in pairs evenly distributed over the circumference, one pair of which serves to continue the air duct and the other leads directly into the propellant gas duct.
- One pair of valves, one valve to the air channel and one channel to the propellant gas, is actuated by a common drive, so that the two valves open and close alternately.
- a disadvantage here is the mechanical outlay, in particular due to the large number of valves required. From DE 32 09 135 AI a combustion chamber is known for a gas turbine, in which the air required for combustion is divided into several partial flows, one of which remains unregulated when it ends at a burner.
- the quantity ratio of two further partial flows, a primary air quantity and a secondary air quantity can be controlled depending on the load.
- the control takes place via an adjusting ring and primary air control surfaces and secondary air openings carried by it.
- a targeted oxidation of the fuel is ensured, so that the formation of nitrogen oxides is minimized.
- primary and / or secondary air ducts are also required, which, in addition to an outlay on equipment, also result in a pressure drop for the partial air flow that they each guide.
- Quantity is taxable.
- two superimposed, slotted disks are rotated against each other so that the slots overlap each other to a greater or lesser extent or release more or less flow cross-section for the controlled partial flow of air.
- the invention is based on the object of creating a gas fitting for a gas turbine plant which is equally simple and reliable and which at the same time closes a path and opens another path for a gas stream with a very short switchover time.
- transverse bulkhead is provided as a transverse partition wall on at least one side of the common wall, that the transverse bulkhead and, in its region on the compressor side, the common wall by a slide are covered and that corresponding slots in the common wall and in the transverse bulkhead can be alternately closed by slots in the slide.
- the common wall lies between the transverse bulkhead and the mouth of the compressor outlet closed by it and that the slide is L-shaped in cross section.
- the turbine inlet and the compressor outlet lie concentrically one inside the other, the turbine inlet and the compressor outlet being circular or circular in cross-section and the annular slide being movable parallel to the slot surfaces.
- a further advantageous embodiment of the invention is that the slide closes the slots in the transverse bulkhead in an end position and at the same time releases the slots in the common wall, and that the released slots in the common wall represent a bypass channel through which compressed air on the combustion chamber flows directly from the compressor outlet to the turbine inlet.
- the gas fitting according to the invention is very advantageous because it works with a very small number of parts that move against one another and therefore with a very small number of sealing devices, and at the same time enables very short switching distances and therefore also very short switching times and thus rapid reactions .
- FIG 2 shows a section through one of the gas fittings along the line 'II-II and
- a common shaft 7 of a compressor 5 and a turbine 6 carries their blades, not shown.
- the common shaft 7 also carries an extension to the coupling with a machine to be driven, for example an electric generator.
- Compressed air conveyed by the compressor 5 flows in the direction of arrows 8 through a compressor outlet 9 to a gas valve 10 and from there further in normal operation
- a plurality of gas fittings and combustion chambers associated therewith are preferably provided, distributed uniformly over the circumference of the turbine.
- Combustion chambers with fluidized beds for the combustion of solid fuels, for example lignite, hard coal or waste materials, are particularly suitable as the combustion chamber.
- a hot gas which is low in nitrogen oxide and sulfur dioxide is generated in the combustion chamber by known firing and by adding reaction agents.
- the combustion chambers are preferably set up some distance from the turbine, for example in a special building separated from a turbine hall. The hot gas is dedusted in a manner not shown in detail and then flows in the direction of an arrow 12 into the fitting 10.
- Electric motor 20 via a gear 21 and 22 a push rod 23 which moves the slide between its end positions.
- a hydraulic or pneumatic actuating device (not shown in more detail) is also provided for the slide.
- This additional actuating device is superimposed on the first-mentioned drive and is used for the rapid, quasi-sudden switchover of the valve to the position shown in the drawing, in which the slots 17 and 19 are aligned with one another and form a bypass channel for the compressed air which is there ⁇ flows past the combustion chamber directly to the turbine 6.
- the slots 16 are closed in this slide position by webs between the slots 18.
- the slots 16 and 18 are aligned with one another and the slots 17 in the wall 1 are closed by webs between the slots 19.
- the compressed air therefore flows, as already stated above, in the direction of arrows 8 and 11 from the compressor outlet 9 through the gas fitting 10 to the solid-fired combustion chamber and the dedusted hot gas coming from there flows in the direction of the arrows 12 and 24 through the turbine inlet 13 into the turbine 6.
- the slide In part-load operation, the slide is slowly brought into an intermediate position adapted to the respective load condition, in which only part of the compressed air reaches the combustion chamber and the rest of the compressed air reaches the turbine directly through the slots 17 and 19, which in some cases open to one another. As a result, the mass flow in the turbine remains within an acceptable range.
- gas valve according to the invention is suitable both for gas turbine systems with combustion chambers directly attached to compressor 5 and gas turbine 6 and for systems with combustion chambers set up remotely from them.
Abstract
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP95900070A EP0730707B1 (de) | 1993-11-22 | 1994-11-08 | Gasarmatur |
JP7514733A JPH09505389A (ja) | 1993-11-22 | 1994-11-08 | ガス弁 |
DE59409243T DE59409243D1 (de) | 1993-11-22 | 1994-11-08 | Gasarmatur |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DEP4339724.7 | 1993-11-22 | ||
DE4339724A DE4339724C1 (de) | 1993-11-22 | 1993-11-22 | Gasarmatur |
Publications (1)
Publication Number | Publication Date |
---|---|
WO1995014854A1 true WO1995014854A1 (de) | 1995-06-01 |
Family
ID=6503125
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/DE1994/001312 WO1995014854A1 (de) | 1993-11-22 | 1994-11-08 | Gasarmatur |
Country Status (7)
Country | Link |
---|---|
US (1) | US5692370A (de) |
EP (1) | EP0730707B1 (de) |
JP (1) | JPH09505389A (de) |
CN (1) | CN1043373C (de) |
DE (2) | DE4339724C1 (de) |
ES (1) | ES2145248T3 (de) |
WO (1) | WO1995014854A1 (de) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO1998023902A1 (en) * | 1996-11-26 | 1998-06-04 | Alliedsignal Inc. | Combustor dilution bypass system |
Families Citing this family (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE19741197C1 (de) * | 1997-09-18 | 1999-01-28 | Siemens Ag | Adapterarmatur zum Einsatz in einer stationären Gasturbinenanlage |
SE511692C2 (sv) * | 1998-03-27 | 1999-11-08 | Abb Ab | Anordning för att leda in en het gas i en rotormaskin |
US20070151257A1 (en) * | 2006-01-05 | 2007-07-05 | Maier Mark S | Method and apparatus for enabling engine turn down |
AT506592B1 (de) * | 2008-08-26 | 2009-10-15 | Edmund Ing Lorenz | Verbrennungsturbine mit diskontinuierlicher verbrennung |
US8092153B2 (en) * | 2008-12-16 | 2012-01-10 | Pratt & Whitney Canada Corp. | Bypass air scoop for gas turbine engine |
US8316880B2 (en) * | 2009-05-08 | 2012-11-27 | Hamilton Sundstrand Corporation | Oil filter bypass valve assembly for a generator |
RU2506499C2 (ru) * | 2009-11-09 | 2014-02-10 | Дженерал Электрик Компани | Топливные форсунки газовой турбины с противоположными направлениями завихрения |
RU2010101978A (ru) * | 2010-01-15 | 2011-07-20 | Дженерал Электрик Компани (US) | Соединительный узел для газовой турбины |
US8276386B2 (en) | 2010-09-24 | 2012-10-02 | General Electric Company | Apparatus and method for a combustor |
US9297532B2 (en) * | 2011-12-21 | 2016-03-29 | Siemens Aktiengesellschaft | Can annular combustion arrangement with flow tripping device |
EP2868898A1 (de) | 2013-10-30 | 2015-05-06 | Siemens Aktiengesellschaft | Verbesserter Teillastbetrieb einer Gasturbine mit einstellbarem Bypass-Strömungskanal |
DE102015207803A1 (de) * | 2015-04-28 | 2016-11-03 | Siemens Aktiengesellschaft | Gasturbinenanlage |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE2511172A1 (de) * | 1975-03-14 | 1976-09-30 | Daimler Benz Ag | Filmverdampfungs-brennkammer |
GB2017219A (en) * | 1978-03-01 | 1979-10-03 | Stal Laval Turbin Ab | Gas Turbine Plant |
DE3209135A1 (de) * | 1982-03-12 | 1983-09-15 | Kraftwerk Union AG, 4330 Mülheim | Gasturbinenbrennkammer |
EP0239462A1 (de) * | 1986-03-20 | 1987-09-30 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Brennstoffeinspritzeinrichtung mit axial-centripetaler Luftzuführung |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE320135C (de) * | 1920-04-15 | Eickhoff Geb | Stossverbindung fuer Schuettelrinnen | |
CH324502A (de) * | 1954-12-18 | 1957-09-30 | Bbc Brown Boveri & Cie | Selbsttätige Luftregelungseinrichtung bei Brennkammern von Gasturbinenanlagen |
US3986347A (en) * | 1973-12-06 | 1976-10-19 | Phillips Petroleum Company | Combustor process for low-level NOx and CO emissions |
JPS5296420A (en) * | 1976-02-10 | 1977-08-13 | Mitsubishi Heavy Ind Ltd | Burner |
DE2620424C2 (de) * | 1976-05-08 | 1983-07-21 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Brennkammer mit variabler Geometrie der Luftzuführung für Gasturbinentriebwerke |
DE2728399C2 (de) * | 1977-06-24 | 1982-04-22 | Brown, Boveri & Cie Ag, 6800 Mannheim | Brennkammer für eine Gasturbine |
JPS60240832A (ja) * | 1984-05-14 | 1985-11-29 | Kobe Steel Ltd | ガスタ−ビン燃焼器 |
SE456757B (sv) * | 1987-03-09 | 1988-10-31 | Asea Stal Ab | Kraftanlaeggning med foerbraenning vid hoegt tryck och en gasturbin driven av foerbraenningsgaserna |
JPH02197717A (ja) * | 1989-01-25 | 1990-08-06 | Ishikawajima Harima Heavy Ind Co Ltd | 燃焼器 |
DK0480717T3 (da) * | 1990-10-12 | 1999-02-08 | Merck Frosst Canada Inc | Umættede hydroxyalkylquinolinsyrer som leukotrienantagonister |
US5270324A (en) * | 1992-04-10 | 1993-12-14 | Merck Frosst Canada, Inc. | Fluorinated hydroxyalkylquinoline acids as leukotriene antagonists |
-
1993
- 1993-11-22 DE DE4339724A patent/DE4339724C1/de not_active Expired - Fee Related
-
1994
- 1994-11-08 ES ES95900070T patent/ES2145248T3/es not_active Expired - Lifetime
- 1994-11-08 CN CN94194571A patent/CN1043373C/zh not_active Expired - Fee Related
- 1994-11-08 WO PCT/DE1994/001312 patent/WO1995014854A1/de active IP Right Grant
- 1994-11-08 EP EP95900070A patent/EP0730707B1/de not_active Expired - Lifetime
- 1994-11-08 JP JP7514733A patent/JPH09505389A/ja not_active Ceased
- 1994-11-08 DE DE59409243T patent/DE59409243D1/de not_active Expired - Fee Related
-
1996
- 1996-05-22 US US08/651,083 patent/US5692370A/en not_active Expired - Fee Related
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE2511172A1 (de) * | 1975-03-14 | 1976-09-30 | Daimler Benz Ag | Filmverdampfungs-brennkammer |
GB2017219A (en) * | 1978-03-01 | 1979-10-03 | Stal Laval Turbin Ab | Gas Turbine Plant |
DE3209135A1 (de) * | 1982-03-12 | 1983-09-15 | Kraftwerk Union AG, 4330 Mülheim | Gasturbinenbrennkammer |
EP0239462A1 (de) * | 1986-03-20 | 1987-09-30 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Brennstoffeinspritzeinrichtung mit axial-centripetaler Luftzuführung |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO1998023902A1 (en) * | 1996-11-26 | 1998-06-04 | Alliedsignal Inc. | Combustor dilution bypass system |
US6070406A (en) * | 1996-11-26 | 2000-06-06 | Alliedsignal, Inc. | Combustor dilution bypass system |
Also Published As
Publication number | Publication date |
---|---|
DE59409243D1 (de) | 2000-04-27 |
EP0730707B1 (de) | 2000-03-22 |
EP0730707A1 (de) | 1996-09-11 |
ES2145248T3 (es) | 2000-07-01 |
CN1138364A (zh) | 1996-12-18 |
DE4339724C1 (de) | 1995-01-19 |
CN1043373C (zh) | 1999-05-12 |
US5692370A (en) | 1997-12-02 |
JPH09505389A (ja) | 1997-05-27 |
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