EP0088933A1 - Chambre de combustion pour turbine à gaz - Google Patents

Chambre de combustion pour turbine à gaz Download PDF

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Publication number
EP0088933A1
EP0088933A1 EP19830101957 EP83101957A EP0088933A1 EP 0088933 A1 EP0088933 A1 EP 0088933A1 EP 19830101957 EP19830101957 EP 19830101957 EP 83101957 A EP83101957 A EP 83101957A EP 0088933 A1 EP0088933 A1 EP 0088933A1
Authority
EP
European Patent Office
Prior art keywords
secondary air
primary air
control surfaces
gas turbine
combustion chamber
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
EP19830101957
Other languages
German (de)
English (en)
Inventor
Bernard Dr. Becker
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.)
Kraftwerk Union AG
Original Assignee
Kraftwerk Union AG
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 Kraftwerk Union AG filed Critical Kraftwerk Union AG
Publication of EP0088933A1 publication Critical patent/EP0088933A1/fr
Ceased legal-status Critical Current

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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

Definitions

  • the invention relates to a gas turbine combustion chamber according to the preamble of patent claim 1.
  • Such a gas turbine combustion chamber is known from DE-OS 24 60 709.
  • the inflow cross sections for the primary air can be changed by a first adjusting ring assigned to the primary air openings and the inflow cross sections for the secondary air can be changed by a second adjusting ring assigned to the secondary air openings.
  • the two adjusting rings enclosing the flame tube at an axial distance from one another are connected by rods to a common adjusting device, the rods extending in the axial direction distributed over the circumference of the flame tube.
  • the ratio of primary air quantity to secondary air quantity can then be controlled as a function of the load by axially displacing this common adjusting device.
  • the division of the total air volume into primary air volume and secondary air volume can be adapted to the conditions required to reduce emissions.
  • the adjustment device required to control the air quantity distribution is associated with considerable structural outlay.
  • the large number of moving parts results in a certain susceptibility to malfunction of the adjusting device.
  • the invention is therefore based on the object in a gas turbine combustor of the type mentioned Training the control device so that a control of the air volume distribution that is insensitive to faults is made possible with little structural effort.
  • the adjusting device therefore only consists of a single adjusting ring which surrounds the flame tube and carries both the primary air control surfaces assigned to the primary air openings and the secondary air control surfaces assigned to the secondary air openings.
  • This simple configuration which is insensitive to interference, is made possible in that the axial distance between the primary air openings and / or the secondary openings is bridged by primary air channels and / or secondary air channels running axially on the flame tube.
  • a flame tube 4 is arranged coaxially within the combustion chamber housing 1, at least one burner 5 opens into the outer end area thereof and primary air openings 6 are introduced into the jacket in the area of the combustion zone and secondary air openings 7 in the area of the mixing zone.
  • the primary air openings 6 and the secondary air openings 7 form rows of holes running at an axial distance from one another in the circumferential direction of the flame tube 4.
  • the annular space formed between the combustion chamber housing 1 and the flame tube 4 is acted upon by the compressor of the gas turbine with a total amount of air which is introduced into a primary air amount to be introduced into the combustion zone of the flame tube 4 and into the mixing zone of the flame tube 4 to be introduced secondary air volume is divided.
  • the primary air passes through a swirl device 8 of the burner 5 and through the primary air openings 6 into the combustion zone, while the secondary air is conducted through the secondary air openings 7 into the mixing zone.
  • the excess air in the combustion zone must be increased to reduce the nitrogen oxide emission.
  • the air volume distribution must also be changed in the partial load area or at idle speed in such a way that the primary air volume decreases and the secondary air volume increases.
  • differently constructed adjusting devices are provided in the gas turbine combustion chambers shown in FIGS. 1, 3 and 4.
  • the adjusting device for load-dependent control of the ratio of primary air quantity to secondary air quantity consists of an adjusting ring S1 surrounding the flame tube 4 in the region of the secondary air openings 7, which has openings 9 assigned to the secondary air openings 7 and cross-axially on its side facing the primary air openings 6 to the flame tube 4 aligned primary air control surfaces PS1.
  • Each of these primary air control surfaces PS1 can be pivoted in whole or in part in front of the opening of a primary air duct Pk 1, which is fastened to the outer circumference of the flame tube 4 and leads in the axial direction to the associated primary air opening 6 by rotating the adjusting ring S1.
  • the areas lying between the openings 9 act on the inner circumference of the adjusting ring S1 as secondary air control surfaces SS1, through which the secondary air openings 7 can be completely or partially closed when the adjusting ring S1 is rotated accordingly.
  • the ratio of primary air to secondary air can thus be controlled by rotating the adjusting ring S1 by changing the inflow cross sections for the primary air and for the secondary air.
  • the inflow cross sections for the primary air and the secondary air are open in the upper part of the sectional view of FIG. 1 and shown closed in the lower part, while in the partial cross section of FIG. 2 a position is shown in which a primary air control surface PS1 partially closes the opening of a primary air duct Pk1.
  • the adjusting device for load-dependent control of the ratio of primary air quantity to secondary air quantity consists of an adjusting ring S2 surrounding the flame tube 4, which carries the primary air openings 6 assigned primary air control surfaces PS2 and the secondary air openings 7 assigned secondary air control surfaces SS2.
  • the adjusting ring S2 is arranged in a region lying between the primary air openings 6 and the secondary air openings 7.
  • the axial distance between the primary air openings 6 and the assigned primary air control surfaces PS2 is bridged by primary air channels Pk2 running axially on the flame tube 4, while the axial distance between the secondary air openings 7 and the assigned secondary air control surfaces SS2 is bridged by secondary air channels Sk2 running axially on the flame tube 4 .
  • the inflow cross sections for the primary air and the secondary air are opened in the upper part of the sectional view of FIG. 3 and shown closed in the lower part.
  • the adjusting device for load-dependent control of the ratio of primary air quantity to secondary air quantity consists of an adjusting ring S3 which surrounds the flame tube 4 in the area of the primary air openings 6 and which has openings 10 assigned to the primary air openings 6 and on it the secondary air openings? facing side transversely aligned axially to the flame tube 4 secondary air control surfaces SS3.
  • the areas between the openings 10 on the inner circumference of the adjusting ring S3 act as primary air control surfaces PS3, through which the primary air openings 6 can be completely or partially closed when the adjusting ring S3 is rotated accordingly.
  • the secondary air control surfaces SS3 can be pivoted wholly or partially in front of the openings of secondary air channels Sk3, which are fastened to the outer circumference of the flame tube 4 and lead in the axial direction to the associated secondary air openings 7 by rotating the adjusting ring S 3.
  • the inflow cross sections for the primary air and the secondary air are opened in the upper part of the sectional view of FIG. 4 and shown closed in the lower part.
  • the configuration of the adjusting device shown in FIG. 4 is particularly favorable when the total amount of air supplied by the compressor on the side of the burner 5 is introduced into the annular space formed between the burner housing 1 and the flame tube 4 and the openings of the secondary air channels Sk3 without deflecting the air flow are acted upon.
  • the closure hood 2 shown in dash-dotted lines in FIG. 4 is replaced by a diffuser-like inlet part 20, the supply of the total amount of air being indicated by an arrow L.
  • the configuration of the adjusting device shown in FIG. 1 is particularly favorable if - as in Darge case - the total amount of air supplied by the compressor is supplied on the side of the combustion chamber opposite the burner 5 and the openings of the primary air channels Pk1 can be acted upon without deflecting the air flow. These requirements should also be met in a corresponding manner in the configuration of an adjusting device shown in FIG. 5.
  • FIG. 5 shows a flame tube 40, only partially shown in longitudinal section, with a high-temperature-resistant inner lining 41, with primary air openings 60 opening into the combustion zone and with secondary air openings 70 opening into the mixing zone at an axial distance therefrom.
  • the combustion zone is indicated by the contour of a burner flame F. while the primary air supplied through the primary air openings 60 is indicated by an arrow P, the hot combustion gases by an arrow V and the secondary air supplied through the secondary air openings 70 by an arrow S.
  • the adjusting device for load-dependent control of the ratio of primary air quantity to secondary air quantity consists of an adjusting ring S10 which surrounds the flame tube 40 in the area of the secondary air openings 70 at a distance and which carries primary air control surfaces PS10 assigned to primary air openings 60 and secondary air control surfaces SS10 assigned to secondary air openings 70.
  • the primary air control surfaces PS10 aligned transversely to the flame tube 40 and fastened to the inner circumference of the adjusting ring S10 can be pivoted in whole or in part by rotating the adjusting ring 810 in front of the opening of a primary air channel Pk10, which is fastened to the outer circumference of the flame tube 40 and in the axial direction to the associated one Primary air opening 60 leads.
  • the extending in the circumferential direction of the flame tube 40 and Secondary air control surfaces SS10 fastened on the inner circumference of the adjusting ring S10 via spacer tubes 11 can be pivoted in whole or in part in front of the assigned secondary air openings 70 by rotating the adjusting ring S10.
  • the inflow cross sections for the primary air P and the inflow cross sections for the secondary air S can also be changed by axially displacing the adjusting ring S10 or by a combination of rotation and axial displacement.
  • the secondary air control surfaces SS10 In order to avoid overheating of the secondary air control surfaces SS10, they are provided with a multiplicity of cooling air bores 12, through which, however, only a small amount of air reaches the flame tube 40.
  • the collar S10 which is polygonal in cross section, is mounted on the flame tube 40 in a rolling manner, which cannot be seen to simplify the drawing.
  • the control of the air volume distribution by rotating the adjusting ring S10 is indicated by a double arrow D. From the drawing it can also be seen that the space available between its inner circumference and the outer circumference of the flame tube 40 for supplying the primary air P or the secondary air S is increased by the polygonal cross section of the adjusting ring S10.
  • the primary air control surfaces PS10 and the secondary air control surfaces SS10 are arranged on the adjusting ring S10 such that when the turbine load is increased and the adjusting ring S10 is rotated accordingly, the inflow cross sections for the secondary air S are partially closed before the opening of the inflow cross sections for the primary air P begins.
  • the primary air portion supplied by the swirl device of the burner can be increased.
  • the setting ring S10 can be rotated by means of a motor, pneumatic or hydraulic drive which is arranged outside the combustion chamber housing and is articulated at a point on the setting ring S10 via a corresponding linkage.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Separation By Low-Temperature Treatments (AREA)
EP19830101957 1982-03-12 1983-02-28 Chambre de combustion pour turbine à gaz Ceased EP0088933A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19823209135 DE3209135A1 (de) 1982-03-12 1982-03-12 Gasturbinenbrennkammer
DE3209135 1982-03-12

Publications (1)

Publication Number Publication Date
EP0088933A1 true EP0088933A1 (fr) 1983-09-21

Family

ID=6158125

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19830101957 Ceased EP0088933A1 (fr) 1982-03-12 1983-02-28 Chambre de combustion pour turbine à gaz

Country Status (3)

Country Link
EP (1) EP0088933A1 (fr)
JP (1) JPS58168821A (fr)
DE (1) DE3209135A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1999014533A1 (fr) * 1997-09-18 1999-03-25 Siemens Aktiengesellschaft Garniture d'adaptateur pour ensemble turbine a gaz fixe
RU2531477C1 (ru) * 2013-08-30 2014-10-20 Федеральное государственное казенное военное образовательное учреждение высшего профессионального образования "Военный учебно-научный центр Военно-воздушных сил "Военно-воздушная академия имени профессора Н.Е. Жуковского и Ю.А. Гагарина" (г. Воронеж) Министерства обороны Российской Федерации Устройство для сжигания топлива в газотурбинном двигателе
EP4008958A1 (fr) * 2020-12-07 2022-06-08 Deutsches Zentrum für Luft- und Raumfahrt e.V. Système de chambre de combustion de turbine à gaz et procédé de fonctionnement d'un système de chambre de combustion de turbine à gaz

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6287731A (ja) * 1985-10-14 1987-04-22 Mitsubishi Heavy Ind Ltd 低ｎｏｘ燃焼方法
DE3942451A1 (de) * 1989-12-22 1991-06-27 Daimler Benz Ag Vorrichtung zur einstellung der sekundaerluftmenge an einer gasturbinenbrennkammer
DE4034711C1 (en) * 1990-11-01 1992-02-27 Daimler-Benz Aktiengesellschaft, 7000 Stuttgart, De Secondary air feed control for gas turbine burner flame tube - has jacketed tube with spherical surface in region with air ports with throttle ring
DE4339724C1 (de) * 1993-11-22 1995-01-19 Siemens Ag Gasarmatur
DE102014204482A1 (de) 2014-03-11 2015-09-17 Rolls-Royce Deutschland Ltd & Co Kg Brennkammer einer Gasturbine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE956453C (de) * 1954-12-18 1957-01-17 Bbc Brown Boveri & Cie Selbsttaetige Luftregelungseinrichtung bei Brennkammern von Gasturbinenanlagen
FR2256313A2 (fr) * 1974-01-02 1975-07-25 United Aircraft Canada
DE2460709A1 (de) * 1974-02-04 1975-08-07 Gen Motors Corp Brennkammer fuer gasturbinen
US3958413A (en) * 1974-09-03 1976-05-25 General Motors Corporation Combustion method and apparatus

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3930368A (en) * 1974-12-12 1976-01-06 General Motors Corporation Combustion liner air valve
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

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE956453C (de) * 1954-12-18 1957-01-17 Bbc Brown Boveri & Cie Selbsttaetige Luftregelungseinrichtung bei Brennkammern von Gasturbinenanlagen
FR2256313A2 (fr) * 1974-01-02 1975-07-25 United Aircraft Canada
DE2460709A1 (de) * 1974-02-04 1975-08-07 Gen Motors Corp Brennkammer fuer gasturbinen
US3958413A (en) * 1974-09-03 1976-05-25 General Motors Corporation Combustion method and apparatus

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1999014533A1 (fr) * 1997-09-18 1999-03-25 Siemens Aktiengesellschaft Garniture d'adaptateur pour ensemble turbine a gaz fixe
US6205767B1 (en) 1997-09-18 2001-03-27 Siemens Aktiengesellschaft Adapter fitting for use with a gas turbine and fluidized-bed furnace
RU2531477C1 (ru) * 2013-08-30 2014-10-20 Федеральное государственное казенное военное образовательное учреждение высшего профессионального образования "Военный учебно-научный центр Военно-воздушных сил "Военно-воздушная академия имени профессора Н.Е. Жуковского и Ю.А. Гагарина" (г. Воронеж) Министерства обороны Российской Федерации Устройство для сжигания топлива в газотурбинном двигателе
EP4008958A1 (fr) * 2020-12-07 2022-06-08 Deutsches Zentrum für Luft- und Raumfahrt e.V. Système de chambre de combustion de turbine à gaz et procédé de fonctionnement d'un système de chambre de combustion de turbine à gaz

Also Published As

Publication number Publication date
DE3209135A1 (de) 1983-09-15
JPS58168821A (ja) 1983-10-05

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

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Designated state(s): CH DE FR GB LI SE

17P Request for examination filed

Effective date: 19831007

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

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18R Application refused

Effective date: 19841105

RIN1 Information on inventor provided before grant (corrected)

Inventor name: BECKER, BERNARD, DR.