EP0590338A1 - Gas turbine combustion chamber - Google Patents

Gas turbine combustion chamber Download PDF

Info

Publication number
EP0590338A1
EP0590338A1 EP93114040A EP93114040A EP0590338A1 EP 0590338 A1 EP0590338 A1 EP 0590338A1 EP 93114040 A EP93114040 A EP 93114040A EP 93114040 A EP93114040 A EP 93114040A EP 0590338 A1 EP0590338 A1 EP 0590338A1
Authority
EP
European Patent Office
Prior art keywords
gas turbine
combustion chamber
convective
turbine combustion
cooling
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Withdrawn
Application number
EP93114040A
Other languages
German (de)
French (fr)
Inventor
Rolf Dr. Althaus
Burkhard Schulte-Wrening
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.)
ABB Asea Brown Boveri Ltd
ABB AB
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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
Application filed by ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Publication of EP0590338A1 publication Critical patent/EP0590338A1/en
Withdrawn legal-status Critical Current

Links

Images

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
    • F23R3/005—Combined with pressure or heat exchangers
    • 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
    • F23R3/04—Air inlet arrangements

Definitions

  • the invention relates to a gas turbine combustor in which combinations of convective heat transfer mechanisms are used for cooling, the basic principle of which is the heat dissipation by flow.
  • Such gas turbine combustors are known.
  • the to implement the above The basic principle of the necessary cooling air speed is caused by a drop in pressure. Due to the friction effects in the cooling channels, part of the kinetic energy of the cooling medium is irreversibly converted into heat, thereby reducing the total pressure.
  • the invention tries to avoid all these disadvantages. It is based on the task of designing the transition from the convective cooling duct to the plenum of the burner in a gas turbine combustion chamber in such a way that the total pressure loss in the overall system is reduced. Furthermore, it is based on the additional task of creating an increased design scope for convective cooling measures of the combustion chamber walls, so that the efficiency of the gas turbine is improved compared to the prior art.
  • Fig. 1 part of the gas turbine combustor is shown. It consists of the outer jacket 1, which has to absorb the pressure forces and the inner jacket 2, which is directly exposed to the hot combustion gases. Between the outer jacket 1 and the inner jacket 2, the cooling air flows, which keeps the inner jacket 2 at the temperature necessary for strength and cools it slightly.
  • the fuel nozzle 3 atomizes the fuel under pressure.
  • the transition from the convective cooling duct 4 to the plenum in front of the environmentally friendly burner 5 is formed by the small diffuser 6, which serves to delay the cooling air flow and to recover part of the pressure.
  • the small diffuser 6 has a channel height of 10 mm at the end of the cooling section.
  • the usual diffuser design diagrams for optimal pressure recovery result in an opening angle of 4.3 ° and a length of 40 mm. These sizes can easily be realized in a conventional combustion chamber design.
  • the advantage of the invention is that, compared to the prior art, the total pressure loss in the overall system is reduced. This leads to an improved efficiency of the gas turbine plant. No cooling measures are required in the extended room, since there is no heat input from the combustion.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)

Abstract

In a gas turbine combustion chamber in which cooling is performed by combinations of convective heat transfer mechanisms, the basic principle of which is heat dissipation by flow, the transition from the convective cooling duct (4) to the plenum ahead of the burners (5) is designed as a small diffusor (6). The total pressure loss in the overall system is thereby reduced and this leads to improved efficiency. <IMAGE>

Description

Technisches GebietTechnical field

Die Erfindung betrifft eine Gasturbinenbrennkammer, bei welcher zur Kühlung Kombinationen von konvektiven Wärmeübertragungsmechanismen verwendet werden, deren Grundprinzip die Wärmeabfuhr durch Strömung ist.The invention relates to a gas turbine combustor in which combinations of convective heat transfer mechanisms are used for cooling, the basic principle of which is the heat dissipation by flow.

Stand der TechnikState of the art

Derartige Gasturbinenbrennkammern sind bekannt. Die zur Realisierung des o.g. Grundprinzips notwendige Kühlluftgeschwindigkeit wird dabei durch einen Druckabfall hervorgerufen. Auf Grund der Reibungseffekte in den Kühlkanälen wird grundsätzlich ein Teil der kinetischen Energie des Kühlmediums irreversibel in Wärme umgewandelt und dadurch der Totaldruck reduziert.Such gas turbine combustors are known. The to implement the above The basic principle of the necessary cooling air speed is caused by a drop in pressure. Due to the friction effects in the cooling channels, part of the kinetic energy of the cooling medium is irreversibly converted into heat, thereby reducing the total pressure.

Für hohe Wärmeübertragungseigenschaften der Kühlluft sind grosse Geschwindigkeiten und damit überproportional hohe dynamische Drücke im Strömungskanal erforderlich.High speeds and thus disproportionately high dynamic pressures in the flow channel are required for high heat transfer properties of the cooling air.

Der Übergang vom Konvektivkühlkanal zum Plenum vor den Brennern erfolgte bisher durch unstetige Erweiterung des Strömungsquerschnittes. Der Nachteil an diesem Stand der Technik ist, dass damit ein fast vollständiger Verlust des dynamischen Druckes verbunden ist. Das führt zu einem entsprechenden prozesswirksamen Totaldruckverlust. Das schlägt sich in einer Reduzierung von Wirkungsgrad und Leistung der Gasturbinenanlage nieder.The transition from the convective cooling duct to the plenum in front of the burners has so far been made by an inconsistent expansion of the flow cross-section. The disadvantage of this prior art is that there is an almost complete loss of dynamic Pressure is connected. This leads to a corresponding process-effective total pressure loss. This is reflected in a reduction in the efficiency and performance of the gas turbine system.

Darstellung der ErfindungPresentation of the invention

Die Erfindung versucht all diese Nachteile zu vermeiden. Ihr liegt die Aufgabe zugrunde, bei einer Gasturbinenbrennkammer den Übergang vom Konvektivkühlkanal zum Plenum des Brenners so zu gestalten, dass der Totaldruckverlust im Gesamtsystem vermindert wird. Desweiteren liegt ihr noch die zusätzliche Aufgabe zugrunde, einen erweiterten Gestaltungsspielraum für konvektive Kühlmassnahmen der Brennkammerwände zu schaffen, so dass der Wirkungsgrad der Gasturbine im Vergleich zum Stand der Technik verbessert wird.The invention tries to avoid all these disadvantages. It is based on the task of designing the transition from the convective cooling duct to the plenum of the burner in a gas turbine combustion chamber in such a way that the total pressure loss in the overall system is reduced. Furthermore, it is based on the additional task of creating an increased design scope for convective cooling measures of the combustion chamber walls, so that the efficiency of the gas turbine is improved compared to the prior art.

Erfindungsgemäss wird dies dadurch erreicht, dass der Übergang vom Konvektivkühlkanal zum Plenum vor den Brennern als Kleindiffusor ausgebildet ist.This is achieved according to the invention in that the transition from the convective cooling duct to the plenum in front of the burners is designed as a small diffuser.

Die Vorteile der Erfindung sind unter anderem in der Reduzierung des bisher üblichen fast vollständigen dynamischen Druckverlustes zu sehen. Die erfindungsgemässe Gestaltung des Übergangs vom Konvektivkühlkanal zum Plenum vor den Brennern in Form eines Kleindiffusors führt gleichzeitig zu einem grösseren Gestaltungsspielraum für konvektive Kühlmassnahmen der Brennkammerwände und damit zu einer Erhöhung des Wirkungsgrades der Gasturbinenanlage.The advantages of the invention can be seen, inter alia, in the reduction of the almost complete dynamic pressure loss that has been used up to now. The inventive design of the transition from the convective cooling duct to the plenum in front of the burners in the form of a small diffuser simultaneously leads to greater design freedom for convective cooling measures in the combustion chamber walls and thus to an increase in the efficiency of the gas turbine system.

Kurze Beschreibung der ZeichnungBrief description of the drawing

In der Zeichnung ist ein Ausführungsbeispiel der Erfindung dargestellt. Die einzige Figur zeigt einen Teillängsschnitt durch die Gasturbinenbrennkammer.In the drawing, an embodiment of the invention is shown. The only figure shows a partial longitudinal section through the gas turbine combustion chamber.

Es sind nur die für das Verständnis der Erfindung wesentlichen Elemente gezeigt. Die Strömungsrichtung des Arbeitsmittels ist mit Pfeilen bezeichnet.Only the elements essential for understanding the invention are shown. The direction of flow of the working fluid is indicated by arrows.

Weg zur Ausführung der ErfindungWay of carrying out the invention

In Fig. 1 ist ein Teil der Gasturbinenbrennkammer dargestellt. Sie besteht aus dem äusseren Mantel 1, der die Druckkräfte aufzunehmen hat und dem inneren Mantel 2, der den heissen Verbrennungsgasen direkt ausgesetzt ist. Zwischen dem äusseren Mantel 1 und dem inneren Mantel 2 fliesst die Kühlluft, welche den inneren Mantel 2 auf der für die Festigkeit notwendigen Temperatur hält und geringfügig kühlt. Die Brennstoffdüse 3 zerstäubt den unter Druck stehenden Brennstoff.In Fig. 1, part of the gas turbine combustor is shown. It consists of the outer jacket 1, which has to absorb the pressure forces and the inner jacket 2, which is directly exposed to the hot combustion gases. Between the outer jacket 1 and the inner jacket 2, the cooling air flows, which keeps the inner jacket 2 at the temperature necessary for strength and cools it slightly. The fuel nozzle 3 atomizes the fuel under pressure.

Den Übergang vom Konvektivkühlkanal 4 zum Plenum vor dem umweltfreundlichen Brenner 5 bildet erfindungsgemäss der Kleindiffusor 6, welcher zur Verzögerung der Kühlluftströmung und zum Rückgewinn eines Teils des Druckes dient.According to the invention, the transition from the convective cooling duct 4 to the plenum in front of the environmentally friendly burner 5 is formed by the small diffuser 6, which serves to delay the cooling air flow and to recover part of the pressure.

Mit der Forderung eines minimalen Rückgewinns von 50 % des dynamischen Druckes gibt eine einfache Überschlagsrechnung die geometrische Auslegung des Kleindiffusors 6 an.With the requirement of a minimal recovery of 50% of the dynamic pressure, a simple rollover calculation specifies the geometric design of the small diffuser 6.

In einem Ausführungsbeispiel hat der Kleindiffusor 6 eine Kanalhöhe von 10 mm am Ende der Kühlstrecke. Bei einem vorgegebenen Erweiterungsverhältnis von 1,6 ergibt sich aus den üblichen Diffusorauslegungsdiagrammen für optimalen Druckrückgewinn ein Öffnungswinkel von 4,3° und eine Länge von 40 mm. Diese Grössen sind in einer üblichen Brennkammerkonstruktion ohne weiteres zu realisieren.In one embodiment, the small diffuser 6 has a channel height of 10 mm at the end of the cooling section. With a given expansion ratio of 1.6, the usual diffuser design diagrams for optimal pressure recovery result in an opening angle of 4.3 ° and a length of 40 mm. These sizes can easily be realized in a conventional combustion chamber design.

Der Vorteil der Erfindung besteht darin, dass im Vergleich zum Stand der Technik der Totaldruckverlust im Gesamtsystem vermindert wird. Das führt zu einem verbesserten Wirkungsgrad der Gasturbinenanlage. Im erweiterten Raum sind keine Kühlmassnahmen erforderlich, da keine Wärmezufuhr durch die Verbrennung auftritt.The advantage of the invention is that, compared to the prior art, the total pressure loss in the overall system is reduced. This leads to an improved efficiency of the gas turbine plant. No cooling measures are required in the extended room, since there is no heat input from the combustion.

BezugszeichenlisteReference list

11
äusserer Mantelouter coat
22nd
innerer Mantelinner coat
33rd
BrennstoffdüseFuel nozzle
44th
KonvektivkühlkanalConvective cooling duct
55
Brennerburner
66
KleindiffusorSmall diffuser

Claims (1)

Gasturbinenbrennkammer, bei welcher zur Kühlung Kombinationen von konvektiven Wärmeübertragungsmitteln angeordnet sind, deren Grundprinzip die Wärmeabfuhr durch Strömung ist, dadurch gekennzeichnet, dass der Übergang vom Konvektivkühlkanal (4) zum Plenum vor den Brennern (5) als Kleindiffusor (6) ausgebildet ist.Gas turbine combustion chamber, in which combinations of convective heat transfer means are arranged for cooling, the basic principle of which is heat dissipation by flow, characterized in that the transition from the convective cooling duct (4) to the plenum in front of the burners (5) is designed as a small diffuser (6).
EP93114040A 1992-09-28 1993-09-02 Gas turbine combustion chamber Withdrawn EP0590338A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19924232442 DE4232442A1 (en) 1992-09-28 1992-09-28 Gas turbine combustion chamber
DE4232442 1992-09-28

Publications (1)

Publication Number Publication Date
EP0590338A1 true EP0590338A1 (en) 1994-04-06

Family

ID=6469012

Family Applications (1)

Application Number Title Priority Date Filing Date
EP93114040A Withdrawn EP0590338A1 (en) 1992-09-28 1993-09-02 Gas turbine combustion chamber

Country Status (3)

Country Link
EP (1) EP0590338A1 (en)
JP (1) JPH06221555A (en)
DE (1) DE4232442A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH699309A1 (en) * 2008-08-14 2010-02-15 Alstom Technology Ltd Thermal machine with air cooled, annular combustion chamber.

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19523094A1 (en) * 1995-06-26 1997-01-02 Abb Management Ag Combustion chamber
DE19720786A1 (en) * 1997-05-17 1998-11-19 Abb Research Ltd Combustion chamber

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2482E (en) * 1902-04-30 1904-04-27 Gaston Charles Emile De Bonnec Continuous combustion turbo-engine system
US4288980A (en) * 1979-06-20 1981-09-15 Brown Boveri Turbomachinery, Inc. Combustor for use with gas turbines
JPS60185025A (en) * 1984-03-02 1985-09-20 Hitachi Ltd Liner of combustor for regenerative cycle gas turbine
EP0491625A1 (en) * 1990-12-19 1992-06-24 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Short length, low NOx, reverse flow combustion chamber

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2155835B1 (en) * 1971-10-08 1974-05-31 Snecma
US3751910A (en) * 1972-02-25 1973-08-14 Gen Motors Corp Combustion liner
US4297842A (en) * 1980-01-21 1981-11-03 General Electric Company NOx suppressant stationary gas turbine combustor
JPH0752014B2 (en) * 1986-03-20 1995-06-05 株式会社日立製作所 Gas turbine combustor
GB2221979B (en) * 1988-08-17 1992-03-25 Rolls Royce Plc A combustion chamber for a gas turbine engine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2482E (en) * 1902-04-30 1904-04-27 Gaston Charles Emile De Bonnec Continuous combustion turbo-engine system
US4288980A (en) * 1979-06-20 1981-09-15 Brown Boveri Turbomachinery, Inc. Combustor for use with gas turbines
JPS60185025A (en) * 1984-03-02 1985-09-20 Hitachi Ltd Liner of combustor for regenerative cycle gas turbine
EP0491625A1 (en) * 1990-12-19 1992-06-24 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Short length, low NOx, reverse flow combustion chamber

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 10, no. 29 (M - 451)<2086> 5 February 1986 (1986-02-05) *

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH699309A1 (en) * 2008-08-14 2010-02-15 Alstom Technology Ltd Thermal machine with air cooled, annular combustion chamber.
EP2154431A2 (en) * 2008-08-14 2010-02-17 Alstom Technology Ltd Thermal machine
EP2154431A3 (en) * 2008-08-14 2010-08-04 Alstom Technology Ltd Thermal machine

Also Published As

Publication number Publication date
DE4232442A1 (en) 1994-03-31
JPH06221555A (en) 1994-08-09

Similar Documents

Publication Publication Date Title
DE3889301T2 (en) Combustion chamber to reduce pollutant emissions from gas turbines.
DE4406399B4 (en) heat generator
EP0599055B1 (en) Gasturbine combustor
CH687269A5 (en) Gas turbine group.
DE19501471A1 (en) Internal combustion gas turbine
EP0781967A2 (en) Annular combustion chamber for gas turbine
EP0731255A1 (en) Powerplant system
EP1243757A1 (en) Process for operating a power plant
DE69101389T2 (en) Solid and liquid or gaseous fuel burners.
EP0666412B1 (en) Method for cooling the cooling air for a gasturbine
DE4242721A1 (en) Gas turbine combustion chamber
EP0590338A1 (en) Gas turbine combustion chamber
DE19900026A1 (en) Gas turbine with direct steam injection has compressor unit supplied with steam, water from waste heat steam generator, or fresh water from outside
EP0611879A1 (en) Cooling means for a gas turbine
DE874678C (en) Pipe gas heaters, especially for solid fuels, preferably for use in two-stage gas turbine plants
DE2200102B2 (en) Device for generating a working gas flow
EP0602404B1 (en) Gas turbine combustor
DE976379C (en) Circulating regenerative air preheater divided into two or more stages
DE944647C (en) Gas turbine plant with rotating, ring-shaped regenerator
DE975112C (en) Steam temperature control in a radiant steam generator
DE2052905A1 (en) Heat exchanger
AT402439B (en) DEVICE FOR EXHAUST GAS RECIRCULATION AT A COMBUSTION CHAMBER
DE2320594B2 (en) Dual-circuit jet engine
DE2053805B2 (en) Recuperative burner for industrial furnace - has air duct extending around combustion chamber with flow reversed past this to burner
CH330986A (en) Gas turbine plant

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 19941007