EP0899510A2 - Boítier répartiteur d'air pour chambre de combustion - Google Patents

Boítier répartiteur d'air pour chambre de combustion Download PDF

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Publication number
EP0899510A2
EP0899510A2 EP98810828A EP98810828A EP0899510A2 EP 0899510 A2 EP0899510 A2 EP 0899510A2 EP 98810828 A EP98810828 A EP 98810828A EP 98810828 A EP98810828 A EP 98810828A EP 0899510 A2 EP0899510 A2 EP 0899510A2
Authority
EP
European Patent Office
Prior art keywords
flow
plenum
wall
gas
gas flows
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.)
Granted
Application number
EP98810828A
Other languages
German (de)
English (en)
Other versions
EP0899510A3 (fr
EP0899510B1 (fr
Inventor
Jakob Prof. Dr. Keller
Hugh Dr. Jackson
Ulf Dr. Müller
Bettina Dr. Paikert
Khawar Dr. Syed
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.)
General Electric Technology GmbH
Original Assignee
ABB Schweiz AG
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 Schweiz AG, ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Schweiz AG
Publication of EP0899510A2 publication Critical patent/EP0899510A2/fr
Publication of EP0899510A3 publication Critical patent/EP0899510A3/fr
Application granted granted Critical
Publication of EP0899510B1 publication Critical patent/EP0899510B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners

Definitions

  • the invention relates to a plenum according to the preamble of the first claim.
  • the heart of the energy conversion in gas turbine systems is the combustion chamber, in which gas and / or liquid fuel is mixed with pre-compressed air and ignited.
  • the combustion of the fuel atomized in air should take place as completely as possible, so that the entire fuel burns while developing the highest possible temperatures.
  • On the one hand carries a residue-free as possible combustion of the fuel to an optimal conversion of energy for, whereby the efficiency of the entire gas-turbine plant is essentially determined
  • the emission gases NO x and CO 2 can gases are considerably reduced at the highest possible combustion temperatures, whereby the environmental loadstrictt positive can be influenced.
  • a housing G is shown in FIG. 1 a, into which the inlet openings 4, 5 Gas streams 1, 2 are blown in.
  • the velocity disappears on a statistical average.
  • they reach the border streamlines Partial beams 1, 2 that pass through the impact point A at this point the same static pressure.
  • the total pressure be the same on both marginal streamlines.
  • the two partial beams experience 1, 2 on their way from the compressor diffuser, through the cooling system of the Combustion chamber to the air hood / plenum of the combustion chamber different Frictional losses because the entry speeds into the plenum 6 of the combustion chamber are not exactly the same.
  • the partial beams 1, 2 different total pressures. Due to the total pressure difference between the two Partial beams 1, 2 the impact point A of the two partial beams must be shifted (as shown in Fig. 1b) in the immediate vicinity of the inlet opening of the partial jet with the smaller total pressure.
  • Air supply shown of a burner 9, which is arranged within a plenum 6 is severely impaired.
  • the plenum 6 is surrounded by a housing wall G and points to the left Side two inlet openings 4, 5 for two gas flows 1, 2, which run along the inner wall of the housing 3 are directed into the interior of the plenum 6.
  • the gas flows 1, 2 meet in an area located around the impact point A of which results from a common, free gas flow 7 into the interior of the plenum 6.
  • the common, free gas stream 7 should be in a gap-like shape Enter the inlet opening 8 of the burner 9 and there with gaseous and / or mixed liquid fuel and brought to ignition in a combustion chamber 15 become.
  • the invention has for its object a plenum, in particular the air supply plenum a gas turbine combustion chamber with at least two flow inlets, for introducing gas flows into the plenum, in which the gas flows in essentially guided along the inner wall of the plenum and directed towards each other in this way are that the gas flows after meeting as a free gas flow are directed away from the inner wall in such a way that without great constructive and manufacturing engineering effort the free Can form gas flow as homogeneously as possible, so that the supply to the burner with supply air in a way that is appropriate for the combustion process Lights up the resource conservation and reduction mentioned above the exhaust gas values can be achieved.
  • the measures to be taken should can also be retrofitted to systems that are already in operation.
  • a plenum according to the preamble of claim 1 is such designed that at least one, essentially orthogonal, on the inner wall to the direction of flow of the gas flows guided on the inner wall oriented flow obstacle is provided.
  • the flow obstacle is preferably made of several orthogonal from the inner wall Raised ribs formed, their width and height approximately are of the same size.
  • the hindrance to flow should be on the inner wall detach the gas flow from it, so that the flow-relevant Influencing the wall on the gas flow is reduced.
  • the obstacle opposing the gas flow is said to be kinematic flow energy revoke.
  • the disturbances significantly, so that the air flows into the plenum largely brought together to form uniform, free flows can.
  • An effective way of reducing the kinetic energy of the Gas flows can be achieved with the flow obstacles according to the invention.
  • Another possibility is the kinetic flow energy of the flowing into a plenum Gas flows to the above speed from below 20 m / s can be reduced by shaping the inlet opening areas according to the invention, where the gas flows enter the interior of the plenum, to reach.
  • a plenum according to the preamble of claim 1 is such To design that the inner wall at areas of the flow inlets in the manner of a step that extends the circumference of the inner wall with the step height b is formed, and that the step into the interior of the capsule opposite a, the guide web limiting the gas flow entering the plenum Length I is provided.
  • gas flows are a rib 11 orthogonal to the direction of flow and provided to the housing inner wall 3.
  • Those hitting rib 11 Flow components become essentially perpendicular to the inner wall of the housing 3 in the interior of the plenum 6 in the direction of the burner 9 as free Gas flows 7 deflected.
  • the burner 9 has at least one gap-shaped one Inlet opening 8 through which the free gas flows 7 into the interior of the burner 9 can occur.
  • the plenum 6 has only a single rib 11, which is symmetrical on both sides of the two gas streams 1 and 2 is charged. With this simple orthogonal rib oriented to the direction of flow can cause an uncontrolled inflow of supply air into the burner can be avoided. As in the figure, they are formed by means of Arrows shown, homogeneous flow circuits from the burner Supply air continuously through inlet opening 8. Remains with this measure still a lot of flow energy in the gas streams, yes carries the symmetrical, bilateral loading of the obstacle Gas flows to controlled circulations within the plenum.
  • FIG. 3 shows a further embodiment according to the invention for the controlled Inflow of gas flows into a plenum 6 is provided.
  • a In the area of the flow inlets 4 and 5 with a flow cross section a is the inner wall 3 each with a cross-sectional step 12 with a flow cross-section b trained.
  • the stage 12 Opposite the stage 12 is a guide web 13 Length I provided.
  • the flow velocity can be effectively reduced to values below 20 m / s.
  • the following dimensions must be provided for this: b / a ⁇ 2 and I / b ⁇ 3.
  • FIG. 4b shows an advantageous arrangement of the flow obstacles in the form of individual ones Ribs 11 shown, as it were the arrangement of a known "Avalanche barriers" are the same.
  • the left arrangement shown in Fig. 4b shows individual ribs 11 in plan view, from which it can be seen that the ribs 11 are staggered one behind the other so that they are perpendicular to them impinging gas flow (see arrows) represent a complete obstacle.
  • An arrangement as shown in Fig. 4b leads to a very efficient one Reduction of the flow velocity and separation of the flow from the inner wall of the vessel. Rib dimensions and their height are particularly suitable and width are approximately the same size.
  • FIG. 4b shows the side view of the rib arrangement shown in FIG. 4a.
  • Fig. 5 shows the basic flow of two gas flows 1 and 2, the a rib 11 are deflected accordingly.
  • the cross-sectional representation according to Fig. 5 corresponds to a section through the plenum of a not shown Annular combustion chamber.
  • a rib designed in this way can also be used for any other plenums.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
EP98810828A 1997-08-30 1998-08-21 Boítier répartiteur d'air pour chambre de combustion Expired - Lifetime EP0899510B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19737997A DE19737997A1 (de) 1997-08-30 1997-08-30 Plenum
DE19737997 1997-08-30

Publications (3)

Publication Number Publication Date
EP0899510A2 true EP0899510A2 (fr) 1999-03-03
EP0899510A3 EP0899510A3 (fr) 2000-07-05
EP0899510B1 EP0899510B1 (fr) 2003-09-24

Family

ID=7840746

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98810828A Expired - Lifetime EP0899510B1 (fr) 1997-08-30 1998-08-21 Boítier répartiteur d'air pour chambre de combustion

Country Status (4)

Country Link
US (1) US6055813A (fr)
EP (1) EP0899510B1 (fr)
JP (1) JP4172854B2 (fr)
DE (2) DE19737997A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7861977B1 (en) 2006-03-13 2011-01-04 The United States Of America As Represented By The Secretary Of The Navy Adaptive material actuators for Coanda effect circulation control slots
US8220271B2 (en) * 2008-09-30 2012-07-17 Alstom Technology Ltd. Fuel lance for a gas turbine engine including outer helical grooves
US8220269B2 (en) * 2008-09-30 2012-07-17 Alstom Technology Ltd. Combustor for a gas turbine engine with effusion cooled baffle

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0321809A1 (fr) 1987-12-21 1989-06-28 BBC Brown Boveri AG Procédé pour la combustion de combustible liquide dans un brûleur

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE767313C (de) * 1942-07-11 1952-05-23 Daimler Benz Ag Einrichtung zum Kuehlhalten der Wandung von Brennkammern an Brennkraftturbinen mit Gleichdruckverbrennung
NL71401C (fr) * 1951-03-22
CH343569A (de) * 1955-06-27 1959-12-31 Lucas Industries Ltd Verbrennungseinrichtung für flüssigen Brennstoff
GB1289523A (fr) * 1969-03-17 1972-09-20
GB1335134A (en) * 1970-12-05 1973-10-24 Nissan Motor Combustion apparatus of a gas turbine engine
US3691766A (en) * 1970-12-16 1972-09-19 Rolls Royce Combustion chambers
JPS5129726A (fr) * 1974-09-06 1976-03-13 Mitsubishi Heavy Ind Ltd
DE2728399C2 (de) * 1977-06-24 1982-04-22 Brown, Boveri & Cie Ag, 6800 Mannheim Brennkammer für eine Gasturbine
JPS54144510A (en) * 1978-05-02 1979-11-10 Kobe Steel Ltd Gas turbine combustor
US5363644A (en) * 1989-12-21 1994-11-15 Sundstrand Corporation Annular combustor
US5077969A (en) * 1990-04-06 1992-01-07 United Technologies Corporation Cooled liner for hot gas conduit
CH687831A5 (de) * 1993-04-08 1997-02-28 Asea Brown Boveri Vormischbrenner.
DE4439619A1 (de) * 1994-11-05 1996-05-09 Abb Research Ltd Verfahren und Vorrichtung zum Betrieb eines Vormischbrenners
DE4446945B4 (de) * 1994-12-28 2005-03-17 Alstom Gasbetriebener Vormischbrenner
DE19523094A1 (de) * 1995-06-26 1997-01-02 Abb Management Ag Brennkammer
DE19651881A1 (de) * 1996-12-13 1998-06-18 Asea Brown Boveri Brennkammer mit integrierten Leitschaufeln

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0321809A1 (fr) 1987-12-21 1989-06-28 BBC Brown Boveri AG Procédé pour la combustion de combustible liquide dans un brûleur

Also Published As

Publication number Publication date
DE59809703D1 (de) 2003-10-30
US6055813A (en) 2000-05-02
DE19737997A1 (de) 1999-03-04
EP0899510A3 (fr) 2000-07-05
JPH11125425A (ja) 1999-05-11
EP0899510B1 (fr) 2003-09-24
JP4172854B2 (ja) 2008-10-29

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