EP0807211B1 - Diffuseur annulaire pour la chambre de combustion de turbines a gaz - Google Patents

Diffuseur annulaire pour la chambre de combustion de turbines a gaz Download PDF

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Publication number
EP0807211B1
EP0807211B1 EP96902919A EP96902919A EP0807211B1 EP 0807211 B1 EP0807211 B1 EP 0807211B1 EP 96902919 A EP96902919 A EP 96902919A EP 96902919 A EP96902919 A EP 96902919A EP 0807211 B1 EP0807211 B1 EP 0807211B1
Authority
EP
European Patent Office
Prior art keywords
diffuser
ring
gas turbine
struts
turbine combustion
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 - Lifetime
Application number
EP96902919A
Other languages
German (de)
English (en)
Other versions
EP0807211A1 (fr
Inventor
William Kwan
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
BMW Rolls Royce GmbH
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 BMW Rolls Royce GmbH filed Critical BMW Rolls Royce GmbH
Publication of EP0807211A1 publication Critical patent/EP0807211A1/fr
Application granted granted Critical
Publication of EP0807211B1 publication Critical patent/EP0807211B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • 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
    • 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
    • F23R3/10—Air inlet arrangements for primary air

Definitions

  • the invention relates to a ring diffuser for a gas turbine combustion chamber with at least two lying essentially next to each other in the radial direction annular diffuser channels that viewed in the circumferential direction Have a plurality of air outlets separated from one another by struts.
  • Such a ring diffuser for supplying in particular stepped is known Gas turbine combustors, d. H. such combustion chambers, which next to Main burners also have pilot burners, from US Pat. No. 5,077,967 is used, for example, for the internal diffuser channel in the radial direction Supply of the individual pilot burners, while in the radial direction external diffuser channel, especially the main burner, is supplied with air.
  • the two are ring-shaped Diffuser channels viewed in the circumferential direction as usual through a variety divided by struts. These struts extend between the Inner and outer walls of the respective diffuser channel and serve on the one hand to support these channel walls, on the other hand also for improved Air routing or distribution of the air flow on the also arranged in a ring several burners.
  • the struts in the radial In the direction of adjacent diffuser channels offset from each other are.
  • FIG. 1 shows a partial section through a ring diffuser, and Fig. 2, the partial view X from Fig. 1.
  • annular gas turbine combustor supplied.
  • the inner wall 2a and the outer wall 2b of the ring diffuser 1 are in the air flow direction (Arrow direction 3) initially several guide blades 4 are provided, downstream of which the ring diffuser 1 extends in two in the radial direction R substantially adjacent annular diffuser channels 5a, 5b branches.
  • the radially inner diffuser channel can be, for example supply the pilot burners of the stepped combustion chamber, not shown, while the outer diffuser channel 5b the respective main burner can be assigned.
  • the diffuser channels 5a, 5b a plurality of adjacent air outlets 6a and 6b on the are separated from each other by struts 7. These struts extend between the respective diffuser channels 5a, 5b in the radial direction delimiting walls 2a, 2a 'and 2b, 2b'.
  • each strut 7 of the diffuser channel 5a is viewed in the circumferential direction U in FIG essentially between two struts 7 of the diffuser channel 5b and vice versa.
  • Another advantage of the strut arrangement shown is that the caused by temperature peaks or an uneven temperature distribution Stresses in the component can be reduced. In particular until The walls of the outer are reaching a steady temperature distribution Diffuser channel 5b is still relatively cold, while the walls of the interior Diffuser channel 5a through the hot according to arrow direction 3 from the compressor part the air flow delivered to the gas turbine is already heated.
  • This different temperature distribution can be particularly in the range Merging the walls 2a 'and 2b' lead to stress cracks, in particular if this merging or the two walls 2a ', 2b' themselves are designed to be relatively rigid.
  • the same inventive effects can also be achieved, if, for example, the struts 7 of the inner diffuser channel 5a are not lie exactly between the two struts 7 of the outer diffuser channel 5b, but more or less off-center with respect to each other Air outlet 6b.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (1)

  1. Diffuseur annulaire pour la chambre de combustion d'une turbine à gaz comportant au moins deux canaux de diffuseur (5a, 5b) annulaire, essentiellement juxtaposés dans la direction radiale (R), et qui, vus dans la direction périphérique (U), ont une multiplicité de sorties d'air (6a, 6b) séparées l'une de l'autre par des entretoises (7),
    caractérisé en ce que
    les entretoises (7) des canaux de diffuseur (5a, 5b) juxtaposés dans la direction radiale (R) sont décalées.
EP96902919A 1995-02-03 1996-01-25 Diffuseur annulaire pour la chambre de combustion de turbines a gaz Expired - Lifetime EP0807211B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19503567 1995-02-03
DE19503567A DE19503567A1 (de) 1995-02-03 1995-02-03 Ringdiffusor für eine Gasturbinen-Brennkammer
PCT/EP1996/000299 WO1996023978A1 (fr) 1995-02-03 1996-01-25 Diffuseur annulaire pour la chambre de combustion de turbines a gaz

Publications (2)

Publication Number Publication Date
EP0807211A1 EP0807211A1 (fr) 1997-11-19
EP0807211B1 true EP0807211B1 (fr) 1999-05-19

Family

ID=7753124

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96902919A Expired - Lifetime EP0807211B1 (fr) 1995-02-03 1996-01-25 Diffuseur annulaire pour la chambre de combustion de turbines a gaz

Country Status (4)

Country Link
EP (1) EP0807211B1 (fr)
CA (1) CA2208843A1 (fr)
DE (2) DE19503567A1 (fr)
WO (1) WO1996023978A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11732892B2 (en) 2013-08-14 2023-08-22 General Electric Company Gas turbomachine diffuser assembly with radial flow splitters

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2241840C2 (ru) * 2002-11-12 2004-12-10 Открытое акционерное общество "Авиадвигатель" Газотурбинный двигатель
FR2880391A1 (fr) * 2005-01-06 2006-07-07 Snecma Moteurs Sa Diffuseur pour chambre annulaire de combustion, en particulier pour un turbomoteur d'avion

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2704089A (en) * 1952-06-09 1955-03-15 Lee R Woodworth Gas turbine diffuser
DE1092159B (de) * 1956-12-20 1960-11-03 Messerschmitt Boelkow Blohm Axialverdichter mit relativer UEberschallgeschwindigkeit
GB1315856A (en) * 1970-03-20 1973-05-02 Secr Defence Flow restrictors
US5077967A (en) * 1990-11-09 1992-01-07 General Electric Company Profile matched diffuser
US5165850A (en) * 1991-07-15 1992-11-24 General Electric Company Compressor discharge flowpath
US5323604A (en) * 1992-11-16 1994-06-28 General Electric Company Triple annular combustor for gas turbine engine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11732892B2 (en) 2013-08-14 2023-08-22 General Electric Company Gas turbomachine diffuser assembly with radial flow splitters
US12044408B2 (en) 2013-08-14 2024-07-23 Ge Infrastructure Technology Llc Gas turbomachine diffuser assembly with radial flow splitters

Also Published As

Publication number Publication date
DE19503567A1 (de) 1996-08-08
WO1996023978A1 (fr) 1996-08-08
EP0807211A1 (fr) 1997-11-19
CA2208843A1 (fr) 1996-08-08
DE59601944D1 (de) 1999-06-24

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