EP2201300A1 - Burner for a turbomachine, guide plate for a burner of said kind and turbomachine having burner of said kind - Google Patents
Burner for a turbomachine, guide plate for a burner of said kind and turbomachine having burner of said kindInfo
- Publication number
- EP2201300A1 EP2201300A1 EP08842721A EP08842721A EP2201300A1 EP 2201300 A1 EP2201300 A1 EP 2201300A1 EP 08842721 A EP08842721 A EP 08842721A EP 08842721 A EP08842721 A EP 08842721A EP 2201300 A1 EP2201300 A1 EP 2201300A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- burner
- baffle
- guide plate
- flame chamber
- fastening
- 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
Links
- 125000006850 spacer group Chemical group 0.000 claims abstract description 10
- 239000000463 material Substances 0.000 claims description 10
- 238000001816 cooling Methods 0.000 description 9
- 230000008646 thermal stress Effects 0.000 description 8
- 238000003466 welding Methods 0.000 description 4
- 239000000446 fuel Substances 0.000 description 3
- 238000010276 construction Methods 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 241001156002 Anthonomus pomorum Species 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 230000035882 stress Effects 0.000 description 1
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 object of the present invention is to reduce the thermal stress on a burner for turbomachines while maintaining the proven flow To minimize technical constraints and to create a turbomachine with such a burner.
- a partial flow of air can flow between the fastening section of the guide plate and the wall section of the flame chamber, as a result of which cooling of the wall sections on both sides takes place.
- the wall sections are cooled on their inner surface facing the flame chamber as well as conventionally on their outer surface facing away from the flame chamber.
- welded joints for mounting the baffle are cooled on both sides.
- the spacers may be separate components or represent, for example, elevations of the fastening portion or the wall portion of the flame chamber, which are achieved by a wave-shaped deformation of the fastening portion or the Wandungsabitess.
- a guide plate according to the invention for a burner of a turbomachine has a flow guide edge for guiding an air flow and a fastening section facing away from the flow guide edge for fastening the guide plate to a wall section of the burner.
- the attachment portion shows the attachment portion a plurality of elevations, via which it can be fastened to a wall portion of a flame chamber of a burner.
- the elevations each extend from a fastening edge of the fastening portion to the flow guide edge.
- a plurality of channels is formed between the elevations, which extend substantially in the flow direction of the air flow.
- a partial stream of the injected air can flow with almost no change in direction between the mounting portion of the baffle and the wall portion of the flame chamber.
- the elevations are executed stepwise in the form of a rectangular curve.
- the elevations 48 extend from a fastening edge 54 formed by the long longitudinal side 42 in the direction of the current-carrying edge 34 and merge into a planar current-carrying section 56 which adjoins the fastening section 32.
- the wave troughs 52a, 52b, 52c,... Each have the same geometry and are uniformly distributed over the attachment section 32, so that they run symmetrically on both sides of the attachment section 32.
Landscapes
- 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)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102007050664A DE102007050664A1 (en) | 2007-10-24 | 2007-10-24 | Burner for a turbomachine, baffle for such a burner and a turbomachine with such a burner |
PCT/EP2008/008936 WO2009053049A1 (en) | 2007-10-24 | 2008-10-22 | Burner for a turbomachine, guide plate for a burner of said kind and turbomachine having burner of said kind |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2201300A1 true EP2201300A1 (en) | 2010-06-30 |
EP2201300B1 EP2201300B1 (en) | 2015-06-03 |
Family
ID=40405029
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP08842721.6A Active EP2201300B1 (en) | 2007-10-24 | 2008-10-22 | Burner for a Turbomachine and a Turbomachine |
Country Status (6)
Country | Link |
---|---|
US (1) | US20100205969A1 (en) |
EP (1) | EP2201300B1 (en) |
JP (1) | JP5324588B2 (en) |
CA (1) | CA2696994A1 (en) |
DE (1) | DE102007050664A1 (en) |
WO (1) | WO2009053049A1 (en) |
Family Cites Families (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CH255541A (en) * | 1947-05-12 | 1948-06-30 | Bbc Brown Boveri & Cie | Cooled metal combustion chamber for generating heating and propellant gases. |
US2625792A (en) * | 1947-09-10 | 1953-01-20 | Rolls Royce | Flame tube having telescoping walls with fluted ends to admit air |
US2544538A (en) * | 1948-12-01 | 1951-03-06 | Wright Aeronautical Corp | Liner for hot gas chambers |
DE825777C (en) * | 1949-08-19 | 1951-12-20 | Canadian Patents Dev | Flame tube of combustion chambers, especially for gas turbines |
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 |
US3752225A (en) * | 1970-06-02 | 1973-08-14 | Gen Motors Corp | Duct for hot gas |
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 |
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 |
DE4223733C2 (en) * | 1992-07-18 | 1995-05-18 | Gutehoffnungshuette Man | Connection of mixing tube and flame tube of a gas turbine |
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 |
ES2309029T3 (en) * | 2001-01-09 | 2008-12-16 | Mitsubishi Heavy Industries, Ltd. | GAS TURBINE COMBUSTION CHAMBER. |
JP3924136B2 (en) * | 2001-06-27 | 2007-06-06 | 三菱重工業株式会社 | Gas turbine combustor |
US7631481B2 (en) * | 2004-12-01 | 2009-12-15 | United Technologies Corporation | Cooled duct for gas turbine engine |
-
2007
- 2007-10-24 DE DE102007050664A patent/DE102007050664A1/en not_active Withdrawn
-
2008
- 2008-10-22 WO PCT/EP2008/008936 patent/WO2009053049A1/en active Application Filing
- 2008-10-22 US US12/678,323 patent/US20100205969A1/en not_active Abandoned
- 2008-10-22 EP EP08842721.6A patent/EP2201300B1/en active Active
- 2008-10-22 JP JP2010530336A patent/JP5324588B2/en not_active Expired - Fee Related
- 2008-10-22 CA CA2696994A patent/CA2696994A1/en not_active Abandoned
Non-Patent Citations (1)
Title |
---|
See references of WO2009053049A1 * |
Also Published As
Publication number | Publication date |
---|---|
JP5324588B2 (en) | 2013-10-23 |
WO2009053049A1 (en) | 2009-04-30 |
JP2011501098A (en) | 2011-01-06 |
CA2696994A1 (en) | 2009-04-30 |
EP2201300B1 (en) | 2015-06-03 |
DE102007050664A1 (en) | 2009-04-30 |
US20100205969A1 (en) | 2010-08-19 |
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