US20100205969A1 - Burner for a Turbo Machine, Baffle plate for Such a Burner and a Turbo Machine Having Such a Burner - Google Patents

Burner for a Turbo Machine, Baffle plate for Such a Burner and a Turbo Machine Having Such a Burner Download PDF

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Publication number
US20100205969A1
US20100205969A1 US12/678,323 US67832308A US2010205969A1 US 20100205969 A1 US20100205969 A1 US 20100205969A1 US 67832308 A US67832308 A US 67832308A US 2010205969 A1 US2010205969 A1 US 2010205969A1
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US
United States
Prior art keywords
baffle plate
burner
section
mounting
elevations
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.)
Abandoned
Application number
US12/678,323
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English (en)
Inventor
Emil Aschenbruck
Reiner Brinkmann
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.)
MAN Energy Solutions SE
Original Assignee
MAN Turbo 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 MAN Turbo AG filed Critical MAN Turbo AG
Assigned to MAN TURBO AG reassignment MAN TURBO AG ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: ASCHENBRUCK, EMIL, BRINKMANN, REINER
Assigned to MAN DIESEL & TURBO SE reassignment MAN DIESEL & TURBO SE CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: MAN TURBO AG
Publication of US20100205969A1 publication Critical patent/US20100205969A1/en
Abandoned 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
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03042—Film cooled combustion chamber walls or domes

Definitions

  • the present invention relates to a burner for a turbo machine and more specifically to a burner having a baffle plate for guiding an air stream in a flame chamber.
  • the flame chambers In a combustion process taking place in a flame chamber of a burner for turbo machines, radiant heat is formed, heating up in particular the chamber wall bordering the flame chamber. With thick walls and/or overlapping of material, this heating leads to high thermal stresses.
  • the respective wall sections of the flame chamber are usually cooled by convection, in which outside air is guided over exterior surfaces of wall sections facing away from the flame chamber.
  • the flame chambers are usually made of thin-walled sheet metal constructions such as flame tubes. Changes in cross section or measures to guide the flow of a mixed fuel-air stream or an air stream, such as baffle plates or swirl generators are welded in place.
  • the baffle plates may be designed as conical rings having a mounting section for welding to a wall section of the flame chamber and having a flow guide edge facing away from the mounting section. After welding, the baffle plate with its mounting section is in contact with the wall section of the flame chamber over a large area, thus forming a large-area overlap of material, which promotes the development of thermal stresses. Since the overlap areas can be cooled on only one side, the thermal stresses cannot be adequately reduced.
  • It is an object of the present invention is to minimize the thermal stress associated with a burner for turbo machines while retaining the proven boundary conditions with regard to fluid mechanics and to create a turbo machine having such a burner.
  • An inventive burner for a turbo machine has a flame chamber, a swirl generator for applying a swirl to an air stream and a baffle plate arranged in the flame chamber for flow guidance of the air stream in the flame chamber.
  • the baffle plate has a mounting section for mounting on a wall section of the flame chamber.
  • the mounting section is connected to the wall section of the flame chamber by a plurality of spacers.
  • the connection may traditionally be achieved by welding.
  • the spacers first prevent an overlapping of material over a large area between the mounting section and the baffle plate and the wall section of the flame chamber.
  • a substream of air may flow between the mounting section of the baffle plate and the wall section of the flame chamber, resulting in cooling of both sides of these wall sections.
  • the wall sections are cooled according to the invention on the interior surface facing the flame chamber as well as traditionally on their exterior surface facing away from the flame chamber.
  • welded joints for mounting the baffle plate are cooled on both sides.
  • the spacers may be separate components or may be, for example, elevations on the mounting section or on the wall section of the flame chamber, which are achieved by a corrugated shaping of the mounting section and/or the wall section.
  • the inventive baffle plate for a burner of a turbo machine has a flow guidance edge for guiding an air stream and a mounting section facing away from the flow guidance edge for mounting the baffle plate to a wall section of the burner.
  • the mounting section has a plurality of elevations by which it can be attached to a wall section of a flame chamber of a burner.
  • the elevations each extend from a mounting edge of the mounting section to the flow guidance edge. This forms a plurality of channels between the elevations, extending essentially in the flow direction of the air stream. This has the advantage that a substream of the injected air can flow between the mounting section of the baffle plate and the wall section of the flame chamber virtually without any change in direction.
  • the elevations preferably taper out in the direction of the flow guidance edge and develop into a planar flow guidance section. Retaining the planar flow guidance section with its linear flow guidance edge has the advantage that the proven flow-optimized boundary conditions remain unchanged.
  • the elevations may be designed like corrugations having a plurality of wave crests and wave troughs.
  • the wave troughs serve as the channels for air guidance for convection cooling between the mounting section of the baffle plate and the wall section of the flame chamber.
  • the elevations are designed like steps in the form of a square-wave curve.
  • the wave crests and wave troughs preferably each have a uniform geometry and are uniformly arranged on the mounting section. This allows uniform cooling to be achieved over the circumference of the baffle plate.
  • the baffle plate is a conical baffle plate ring made of a trapezoidal strip of material having one short longitudinal side and one long longitudinal side.
  • the flow guidance edge here is arranged on the short longitudinal side and the mounting edge is arranged on the long longitudinal side.
  • An inventive turbo machine has a burner with a baffle plate, which is spaced a distance away from wall sections of a flame chamber by means of spacers in some areas.
  • FIG. 1 shows a greatly simplified partial longitudinal cross-sectional view through a flame chamber of burner of the present invention
  • FIG. 2 shows a first embodiment of a baffle plate of the present invention
  • FIG. 3 shows a second embodiment of a baffle plate of the present invention
  • FIG. 4 shows a third embodiment of a baffle plate of the present invention.
  • FIG. 5 shows a fourth embodiment of a baffle plate of the present invention.
  • FIG. 1 shows a partial longitudinal sectional view through the burner 2 for a turbo machine in the area of its fuel and air injection.
  • the burner 2 is embodied in a welded sheet metal design and has a flame chamber 4 bordered axially by a circular burner plate 6 .
  • Nozzles (not shown) are arranged in the burner plate 6 to inject a fuel 8 into the flame chamber 4 .
  • the flame chamber 4 opens conically starting from the burner plate 6 and is bordered essentially by a flame tube 10 radially.
  • a swirl generator 12 is provided between the burner plate 6 and the flame tube 10 for injecting air 14 and for applying a swirl to same.
  • the swirl generator 12 extends around the flame chamber 4 radially and is oriented axially with the longitudinal axis 16 of the burner 2 . Because of the conical design of the flame chamber 4 , the swirl generator 12 has an obliquely inclined inlet opening 18 for the air 14 into the flame chamber 4 .
  • a curved edge section 20 of the swirl generator 12 bordering the inlet opening 18 and located a distance away from the burner plate 6 is connected with a butt joint to a conical wall section 22 of the flame chamber 4 .
  • the flame tube 10 is connected to the wall section 22 with a stepped end section 24 , such that an annular space 20 is formed between an edge area 26 of the wall section 22 spaced a distance away from the swirl generator 12 and the stepped end section 24 of the flame tube 10 .
  • the baffle plate 30 of the present invention which is shaped to form a baffle plate ring, is situated in the connecting area of the swirl generator 12 to the wall section 22 .
  • the baffle plate ring 30 is designed with a conical shape and has a mounting section 32 and a flow guidance edge 34 facing away from the mounting section 32 .
  • the baffle plate ring 30 is arranged on an interior surface 36 of the wall section 22 via a mounting section 32 , which is illustrated in greater detail in FIG. 2 , such that the flow guidance edge 34 protrudes into the inlet opening 18 over the edge section 20 of the swirl generator 12 .
  • a plurality of channels are formed between the wall section 22 and the mounting section 32 of the baffle plate ring 30 because of inventive elevations 48 of the mounting section 22 shown in the following FIGS. 2 through 5 .
  • a substream of the air 14 injected through the inlet opening 18 of the swirl generator 12 flows through these channels, thereby cooling by convection the interior surface 36 of the wall section 22 section by section and thus reducing thermal stresses in the baffle plate ring 30 and the wall section 22 .
  • the mounting section 32 of the baffle plate 30 is cooled by the substream of air 14 . Flow of the substream of air 14 into and through the channels is facilitated by a drop in pressure which is established in the channels.
  • the conical sheet metal ring 30 is formed by a trapezoidal material strip 38 .
  • the material strip 38 has one short longitudinal side 40 and one long longitudinal side 42 opposite it.
  • the two longitudinal sides 40 , 42 are connected to one another by two narrow sides 44 , 46 facing away from one another.
  • the narrow sides 44 , 46 are brought into connection for a butt joint to form the sheet metal ring 30 .
  • the short longitudinal side 40 has the flow guidance edge 34 , which is designed to be straight in the unshaped state of the material strip 38 according to the diagram in FIG. 2 .
  • the mounting section 32 extends from the long longitudinal side 36 in the direction of the flow guidance edge 34 . It has a plurality of elevations 48 , which are corrugated in shape, thus forming a plurality of wave crests 50 a , 50 b , 50 c , . . . and wave troughs 52 a , 52 b , 53 c , . . . .
  • the sheet metal ring 30 is attached to the interior surface 36 of the wall section 22 via the wave crests 50 a , 50 b , 50 c , . . . in at least some sections.
  • the mounting is preferably accomplished by means of known welding techniques such as spot welding.
  • the elevations 48 and/or the wave crests 50 a , 50 b , 50 c , . . . thus function as spacers by means of which the mounting section 32 is spaced away from the wall section 22 , so that overlapping of the material over an area is prevented.
  • the wave crests 52 a , 52 b , 52 c , . . . here serve as the above-mentioned channels in FIG. 1 through which the substream of air 14 flows for convection cooling of both sides of wall section 22 .
  • the welded joints for mounting the sheet metal ring 32 are also cooled by the inventive convection cooling taking place in the interior of the flame chamber 4 in the mounting area of the sheet metal ring 30 .
  • the elevations 48 extend from a mounting edge 54 formed by the long longitudinal side 42 in the direction of the flow guidance edge 34 and develop into a plane or flow guidance section 56 which is adjacent to the mounting section 32 .
  • the wave crests 50 a , 50 b , 50 c , . . . run radially outward in the direction of flow through this extent.
  • the wave crests 50 a , 50 b , 50 c , . . . and the wave troughs 52 a , 52 b , 52 c , . . . each have the same geometry and are distributed uniformly over the mounting section 32 so that they run symmetrically on both sides of the mounting section 32 .
  • the wave form of the mounting section 32 is responsible for a certain elasticity of the baffle plate ring 30 , so that in addition to improved cooling, the thermal stresses are better compensated and/or minimized.
  • the uniformity of the wave form described above results in the thermal stresses being uniformly dissipated over the circumference of the baffle plate 30 and no new stresses being introduced into the baffle plate ring 30 .
  • FIGS. 3 , 4 and 5 each show another embodiment of a baffle plate 58 , 60 , 62 of the present invention.
  • the essential difference between these baffle plates 58 , 60 , 62 and the baffle plate 30 illustrated in FIG. 2 consists of the fact that the number of elevations 48 and thus the frequency of the wave form of the mounting section 32 are higher in FIG. 2 through FIG. 5 .
  • a detailed description of baffle plates 58 , 60 , 62 shown in FIGS. 3 , 4 and 5 may thus be omitted.
  • the elevations 48 can be arranged on the mounting section 32 with different geometries and/or uniformly around the circumference of the baffle plate ring 30 , in such a way that the convection cooling is executed with differing intensities over the circumference of the wall section 22 .
  • a stepped design in the form of a square-wave curve or a sawtooth curve can be mentioned as an example of a different geometric arrangement.
  • the channels it is conceivable for the channels to widen in a funnel shape in the direction of the mounting edge, so that an intensified nozzle effect occurs for continuous flow of the substream of air 14 in the channels.
  • the elevations prefferably be designed on wall section 22 and for the mounting section 32 of the baffle plate ring 30 to be planar. Furthermore it is conceivable for the elevations 48 to be replaced by external spacers or those designed separately, arranged between the wall section 22 and a mounting section. Furthermore it should be pointed out that any shapes of a baffle plate 30 are suitable, and the present invention is not limited to a ring shape.
  • a burner for a turbo machine having a baffle plate arranged in a flame chamber is disclosed, said baffle plate acting on a wall section via a spacer, a baffle plate whose mounting section comprises a plurality of elevations for attachment to a wall section of a flame chamber as well as a turbo machine having such a burner.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US12/678,323 2007-10-24 2008-10-22 Burner for a Turbo Machine, Baffle plate for Such a Burner and a Turbo Machine Having Such a Burner Abandoned US20100205969A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102007050664.5 2007-10-24
DE102007050664A DE102007050664A1 (de) 2007-10-24 2007-10-24 Brenner für eine Strömungsmaschine, Leitblech für einen derartigen Brenner sowie eine Strömungsmaschine mit einem derartigen Brenner
PCT/EP2008/008936 WO2009053049A1 (de) 2007-10-24 2008-10-22 Brenner für eine strömungsmaschine, leitblech für einen derartigen brenner sowie eine strömungsmaschine mit einem derartigen brenner

Publications (1)

Publication Number Publication Date
US20100205969A1 true US20100205969A1 (en) 2010-08-19

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Application Number Title Priority Date Filing Date
US12/678,323 Abandoned US20100205969A1 (en) 2007-10-24 2008-10-22 Burner for a Turbo Machine, Baffle plate for Such a Burner and a Turbo Machine Having Such a Burner

Country Status (6)

Country Link
US (1) US20100205969A1 (de)
EP (1) EP2201300B1 (de)
JP (1) JP5324588B2 (de)
CA (1) CA2696994A1 (de)
DE (1) DE102007050664A1 (de)
WO (1) WO2009053049A1 (de)

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2617255A (en) * 1947-05-12 1952-11-11 Bbc Brown Boveri & Cie Combustion chamber for a gas turbine
US2625792A (en) * 1947-09-10 1953-01-20 Rolls Royce Flame tube having telescoping walls with fluted ends to admit air
US3064425A (en) * 1959-10-05 1962-11-20 Gen Motors Corp Combustion liner
US3572031A (en) * 1969-07-11 1971-03-23 United Aircraft Corp Variable area cooling passages for gas turbine burners
US3751910A (en) * 1972-02-25 1973-08-14 Gen Motors Corp Combustion liner
US3854285A (en) * 1973-02-26 1974-12-17 Gen Electric Combustor dome assembly
US5419114A (en) * 1992-07-18 1995-05-30 Man Gutehoffnungshutte Ag Thermoelastic connection of the injector tube and the flame tube of a gas turbine
US20040074236A1 (en) * 2001-06-27 2004-04-22 Shigemi Mandai Gas turbine combustor

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2544538A (en) * 1948-12-01 1951-03-06 Wright Aeronautical Corp Liner for hot gas chambers
DE825777C (de) * 1949-08-19 1951-12-20 Canadian Patents Dev Flammrohr von Brennkammern, insbesondere fuer Gasturbinen
US3752225A (en) * 1970-06-02 1973-08-14 Gen Motors Corp Duct for hot gas
GB1550368A (en) * 1975-07-16 1979-08-15 Rolls Royce Laminated materials
JPS5556521A (en) * 1978-10-23 1980-04-25 Hitachi Ltd Combustion device
GB2204672B (en) * 1987-05-06 1991-03-06 Rolls Royce Plc Combustor
US5704208A (en) * 1995-12-05 1998-01-06 Brewer; Keith S. Serviceable liner for gas turbine engine
GB9623615D0 (en) * 1996-11-13 1997-07-09 Rolls Royce Plc Jet pipe liner
US6199371B1 (en) * 1998-10-15 2001-03-13 United Technologies Corporation Thermally compliant liner
EP1221574B2 (de) * 2001-01-09 2017-12-20 Mitsubishi Heavy Industries, Ltd. Gasturbinenbrennkammer
US7631481B2 (en) * 2004-12-01 2009-12-15 United Technologies Corporation Cooled duct for gas turbine engine

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2617255A (en) * 1947-05-12 1952-11-11 Bbc Brown Boveri & Cie Combustion chamber for a gas turbine
US2625792A (en) * 1947-09-10 1953-01-20 Rolls Royce Flame tube having telescoping walls with fluted ends to admit air
US3064425A (en) * 1959-10-05 1962-11-20 Gen Motors Corp Combustion liner
US3572031A (en) * 1969-07-11 1971-03-23 United Aircraft Corp Variable area cooling passages for gas turbine burners
US3751910A (en) * 1972-02-25 1973-08-14 Gen Motors Corp Combustion liner
US3854285A (en) * 1973-02-26 1974-12-17 Gen Electric Combustor dome assembly
US5419114A (en) * 1992-07-18 1995-05-30 Man Gutehoffnungshutte Ag Thermoelastic connection of the injector tube and the flame tube of a gas turbine
US20040074236A1 (en) * 2001-06-27 2004-04-22 Shigemi Mandai Gas turbine combustor
US7032386B2 (en) * 2001-06-27 2006-04-25 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
12.4 Multistage Axial Compressors, page 2, http://web.mit.edu/16.unified/www/FALL/thermodynamics/notes/node92.html, 2007 *

Also Published As

Publication number Publication date
WO2009053049A1 (de) 2009-04-30
EP2201300A1 (de) 2010-06-30
JP2011501098A (ja) 2011-01-06
EP2201300B1 (de) 2015-06-03
JP5324588B2 (ja) 2013-10-23
DE102007050664A1 (de) 2009-04-30
CA2696994A1 (en) 2009-04-30

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Legal Events

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AS Assignment

Owner name: MAN TURBO AG, GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:ASCHENBRUCK, EMIL;BRINKMANN, REINER;REEL/FRAME:024084/0742

Effective date: 20100210

AS Assignment

Owner name: MAN DIESEL & TURBO SE, GERMANY

Free format text: CHANGE OF NAME;ASSIGNOR:MAN TURBO AG;REEL/FRAME:024855/0220

Effective date: 20100331

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO PAY ISSUE FEE