DE3332959A1 - Device for the control of the combustion in secondary gas jet compressor plants for gas turbines - Google Patents

Device for the control of the combustion in secondary gas jet compressor plants for gas turbines

Info

Publication number
DE3332959A1
DE3332959A1 DE19833332959 DE3332959A DE3332959A1 DE 3332959 A1 DE3332959 A1 DE 3332959A1 DE 19833332959 DE19833332959 DE 19833332959 DE 3332959 A DE3332959 A DE 3332959A DE 3332959 A1 DE3332959 A1 DE 3332959A1
Authority
DE
Germany
Prior art keywords
combustion
air
stage
secondary gas
takes place
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.)
Ceased
Application number
DE19833332959
Other languages
German (de)
Inventor
Horst 6208 Bad Schwalbach Dens
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Priority claimed from DE19833305254 external-priority patent/DE3305254A1/en
Application filed by Individual filed Critical Individual
Priority to DE19833332959 priority Critical patent/DE3332959A1/en
Publication of DE3332959A1 publication Critical patent/DE3332959A1/en
Ceased 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
    • F02C3/32—Inducing air flow by fluid jet, e.g. ejector action
    • 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
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • 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

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Abstract

A cooling is required so that the secondary gas stream compressor plant is protected from damage due to high temperatures, and is achieved where the combustion in the combustion chambers takes place in two stages. In the first stage, the fuel is burnt with a deficiency of air, leading to the formation of CO molecules and thus to a low combustion temperature. In the second stage, shortly before the outlet from the nozzle of the combustion chamber, the addition of the air required for complete combustion takes place, so that the maximum combustion temperature is first reached shortly before, or in, the mouth of the nozzle. The combustion in two stages moreover makes possible the orderly formation of molecules and thus an improvement of the efficiency of the secondary gas jet plant. So that the required compressor power remains as small as possible, the partitions of the plant are to be heat-insulated, so that the heat transfer from the fuel gas to the gas to be forwarded first takes place by the direct contact of both gas streams.

Description

Einrichtung zur Steuerung der Verbrennung In SeXundärgasstreh1ver-Device for controlling the combustion in secondary gas rotary

dichteranlagen fiir Gasturbinen Beschreibung De Erfindung betrifft eine Einrichtung zur Steuerung der Verbrennung in Sekundärgasstrahlverdichtern gem. Anmeldung P 3305 254.9, die die Übertragung der Bewegungsenergie durch die Bildung von chemischen Bindungen fördert und damit den Wirkungsgrad verbessert und die auftretenden hohen Verbrennungstemperaturen auf einen kleinen Teil der Selcundärgasstrahlverdichter beschränkt, so daß die auftretenden Temperaturen mit zur Zeit bekannten Materialien beherrscht werden können.Sealing systems for gas turbines Description of the invention relates to a device for controlling the combustion in secondary gas jet compressors according to. Registration P 3305 254.9, which describes the transfer of kinetic energy through formation promotes chemical bonds and thus improves the efficiency and the occurring high combustion temperatures on a small part of the secondary gas jet compressors limited, so that the temperatures occurring with currently known materials can be mastered.

Die Brennkammer 1 und die Mischvorrichtung 2 werden durch das Rohr 3 mit hochkomprimierter Frischluft versorgt. Mit Hilfe der Steuerklanpe 4 wird die der Brennkammer 1 zugeführte Frischluft so gedrosselt, daß der durch das Rohr 5 zugeführte Brennstoff unter Luftmangel verbrennt. Dadurch kann die Temperatur in der Brennkammer 1 niedrig gehalten werden. Die zur vollkommenen Verbrennung notwendige Luft wird erst in der Mischvorrichtung 2 zugegeben. Dadurch wird bewirkt, daß die hohe Verbrennungstemteratur erst unmittelbar vor bzw. in der Mündung der Treibdüse 6 entsteht und die Temperatur der Treibdüse 6, somit trotz hoher Gastemperatur, niedrig gehalten werden kann.The combustion chamber 1 and the mixing device 2 are through the pipe 3 is supplied with highly compressed fresh air. With the help of the control flange 4, the the combustion chamber 1 supplied fresh air is throttled so that the through the pipe 5 The fuel supplied burns with a lack of air. This allows the temperature in the combustion chamber 1 can be kept low. The one necessary for perfect combustion Air is only added in the mixing device 2. This causes the high combustion temperature only immediately in front of or in the mouth of the propellant nozzle 6 arises and the temperature of the propellant nozzle 6, thus despite the high gas temperature, can be kept low.

In dem nachgeschaltetem Sekundärgasstrahlverdichter wird ähnlich verfahren. Hier dient die Einrichtung allerdings zusätzlich zur Verbesserung des Wirkungsgrades, in dem die Bildung von Molekislen in zwei Stufen gefördert wird.A similar procedure is followed in the downstream secondary gas jet compressor. Here, however, the device also serves to improve the efficiency, in which the formation of molecules is promoted in two stages.

Der aus der Treibdüse 6 austretende Treibgasstrahl saugt durch das Rohr 7 Frischluft und das Rohr 8 Haftstoff an. Die Frischluftmenge wird mit Hilfe der Steuerklanpe 9 so gesteuert, daß die Verbrennung in dem Rohr 10 zunächst unter Luftmangel erfolgt. Damit kann die Temperatur in diesem Bereich niedrig gehalten werden, weil vorwiegend CO Moleküle gebildet werden.The jet of propellant gas emerging from the propellant nozzle 6 sucks through the Pipe 7 fresh air and pipe 8 adhesive. The amount of fresh air is with the help the control flange 9 controlled so that the combustion in the pipe 10 initially below There is a lack of air. This allows the temperature to be kept low in this area because mainly CO molecules are formed.

Das aus dem Rohr 10 austretende starke CO haltige Gas saugt ebenfalls durch das Rohr 7 Frischluft an, wodurch die weitere Verbrennung zu C02 ermöglicht wird.The strong CO-containing gas emerging from the pipe 10 also sucks through the pipe 7 fresh air, which enables further combustion to CO2 will.

Weil die Frischluftzufuhr direkt vor der Treibdüse 11 des nächsten, in der Zeichnung nicht dargestellten Sekundärgasstrahlverdichters erfolgt, findet auch erst hier die vollkommende Verbrennung und damit die may.Because the fresh air supply directly in front of the propellant nozzle 11 of the next, Secondary gas jet compressor, not shown in the drawing, takes place also only here the complete combustion and with it the may.

Temperaturerhöhung statt.Temperature increase instead.

Auf diese Weise ist es möglich, die Sekundärgasstrahlverdichter durch die Steuerung der Verbrennung in zwei Stufen mit der eigenen Verbrennungsluft zu kijhlen und damit zu verhindern, daß die noch nicht verdichtete zu strömende Luft zur Kühlung genutzt wird, was eine Erhöhung der notwendigen Verdichterarbeit zur Folge hätte. Zu diesem Zweck ist es auch wichtig, daß die Trennwände der Anlage -so wärmeisoliert sind, daß die Wärmeubertragung von dem Arbeitsgas auf das zu fördernde tKraftstff-T.uftgemisch erst durch den direkten T<ontakt beider Gasströme erfolgt.In this way it is possible to use the secondary gas jet compressor the control of the combustion in two stages with its own combustion air to cool and thus to prevent the not yet compressed air to be flowing is used for cooling, which increases the required compressor work Consequence would have. For this purpose it is also important that the partitions of the plant -so heat-insulated that the heat transfer from the working gas to the pumped The fuel-air mixture only takes place through the direct contact between the two gas flows.

Außerdem wird auf diese Weise die Bildung von Molekülen in zwei Stufen und damit die Übertragung der Bewegungsenergie des Treibgases auf das zu fördernde Gas durch chemische Bindungen begtinstigt.Also, in this way, the formation of molecules occurs in two stages and thus the transfer of the kinetic energy of the propellant gas to the gas to be pumped Gas promoted by chemical bonds.

Claims (3)

Patentansnriche Q) Einrichtung zur Steuerung der Verbrennung in Sekundärgasstrahlverdichteranlagen für Gasturbinen dadurch gekennzeichnet, daß die Verbrennung in zwei Stufen erfolgt. In der ersten Stufe unter Luftmangelt was zu einem ueberschuß an CO und damit zur geringen Verbrennungstemneratur führt. In der zweiten Stufe wird die zur vollkommenen Verbrennung notwendige Luft zugegeben, was dazu führt, daß die hohen Verbrennungstemperaturen erst unmittelbar vor dem Austritt aus der Treibdüse entstehen, wodurch die Brennkammer bzw. der Sekundärgasstrahlverdichter thermisch entlastet wird. Patent application Q) Device for controlling the combustion in secondary gas jet compressor systems for gas turbines, characterized in that the combustion takes place in two stages. In the first stage in the absence of air, which leads to an excess of CO and thus to low combustion temperature leads. In the second stage it becomes perfect Combustion necessary air is added, which leads to the high combustion temperatures arise immediately before the outlet from the propellant nozzle, whereby the combustion chamber or the secondary gas jet compressor is thermally relieved. 2. Einrichtung zur Steuerung der Verbrennung in SeQundärgasstrahlverdichteranlagen nach AnsDruch 1 dadurch gekennzeichnet, daß der Wirkungsgrad der Anlage dadurch verbessert wird, daß in der ersten Stufe der Verbrennung die Bildung von CO und in der zweiten Stufe die Bildung von CO2 gefördert wird. Dadurch wird bewirkt, daß die Übertragung der Bewegungsenergie des Treibgases auf die zugeführte Luft bzw. das Kraftstoff-Luftgernisch nicht nur auf mechanischen Wege, sondern hauntsächlich durch die Bildung von Molekülen Ubertragen wird. 2. Device for controlling the combustion in secondary gas jet compressor systems according to AnsDruch 1, characterized in that the efficiency of the system thereby it is improved that in the first stage of combustion the formation of CO and in the second stage, the formation of CO2 is promoted. This causes the transfer of the kinetic energy of the propellant gas to the supplied air or the fuel-air mixture not only in a mechanical way, but a lot is transmitted through the formation of molecules. 3. Einrichtung zur Steuerung der Verbrennung in Sekundärgasstrahlverdichteranlagen nach Anspruch 1 dadurch gekennzeichnet, daß die Trennwände der Anlage so isoliert sind, daß die Wärmeiibertragung auf die zugeführte Luft bzw. das Kraftstoff-Luftgemisch erst durch den direkten Kontakt mit dem Treibgasstrom erfolgt. 3. Device for controlling the combustion in secondary gas jet compressor systems according to claim 1, characterized in that the partition walls of the system are insulated in this way are that the heat transfer to the supplied air or the fuel-air mixture only takes place through direct contact with the propellant gas flow.
DE19833332959 1983-02-16 1983-09-13 Device for the control of the combustion in secondary gas jet compressor plants for gas turbines Ceased DE3332959A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE19833332959 DE3332959A1 (en) 1983-02-16 1983-09-13 Device for the control of the combustion in secondary gas jet compressor plants for gas turbines

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19833305254 DE3305254A1 (en) 1983-02-16 1983-02-16 Secondary gas jet compressor installation for gas turbines
DE19833332959 DE3332959A1 (en) 1983-02-16 1983-09-13 Device for the control of the combustion in secondary gas jet compressor plants for gas turbines

Publications (1)

Publication Number Publication Date
DE3332959A1 true DE3332959A1 (en) 1985-03-28

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Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0635681A1 (en) * 1993-07-07 1995-01-25 R. Jan Mowill Single stage premixed constant fuel/air ratio combustor
US5572862A (en) * 1993-07-07 1996-11-12 Mowill Rolf Jan Convectively cooled, single stage, fully premixed fuel/air combustor for gas turbine engine modules
US5613357A (en) * 1993-07-07 1997-03-25 Mowill; R. Jan Star-shaped single stage low emission combustor system
US5628182A (en) * 1993-07-07 1997-05-13 Mowill; R. Jan Star combustor with dilution ports in can portions
US5638674A (en) * 1993-07-07 1997-06-17 Mowill; R. Jan Convectively cooled, single stage, fully premixed controllable fuel/air combustor with tangential admission
WO1998023902A1 (en) * 1996-11-26 1998-06-04 Alliedsignal Inc. Combustor dilution bypass system
US6220034B1 (en) 1993-07-07 2001-04-24 R. Jan Mowill Convectively cooled, single stage, fully premixed controllable fuel/air combustor

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0635681A1 (en) * 1993-07-07 1995-01-25 R. Jan Mowill Single stage premixed constant fuel/air ratio combustor
US5477671A (en) * 1993-07-07 1995-12-26 Mowill; R. Jan Single stage premixed constant fuel/air ratio combustor
US5481866A (en) * 1993-07-07 1996-01-09 Mowill; R. Jan Single stage premixed constant fuel/air ratio combustor
US5572862A (en) * 1993-07-07 1996-11-12 Mowill Rolf Jan Convectively cooled, single stage, fully premixed fuel/air combustor for gas turbine engine modules
US5613357A (en) * 1993-07-07 1997-03-25 Mowill; R. Jan Star-shaped single stage low emission combustor system
US5628182A (en) * 1993-07-07 1997-05-13 Mowill; R. Jan Star combustor with dilution ports in can portions
US5638674A (en) * 1993-07-07 1997-06-17 Mowill; R. Jan Convectively cooled, single stage, fully premixed controllable fuel/air combustor with tangential admission
US5765363A (en) * 1993-07-07 1998-06-16 Mowill; R. Jan Convectively cooled, single stage, fully premixed controllable fuel/air combustor with tangential admission
US6220034B1 (en) 1993-07-07 2001-04-24 R. Jan Mowill Convectively cooled, single stage, fully premixed controllable fuel/air combustor
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

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