EP2864705A1 - Combustion chamber cooling - Google Patents
Combustion chamber coolingInfo
- Publication number
- EP2864705A1 EP2864705A1 EP13729685.1A EP13729685A EP2864705A1 EP 2864705 A1 EP2864705 A1 EP 2864705A1 EP 13729685 A EP13729685 A EP 13729685A EP 2864705 A1 EP2864705 A1 EP 2864705A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- wall
- gas turbine
- turbine combustor
- elements
- 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.)
- Granted
Links
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
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/002—Wall structures
-
- 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
- F23R3/06—Arrangement of apertures along the flame tube
-
- 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/60—Support structures; Attaching or mounting means
-
- 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
- F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
-
- 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
- F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
Definitions
- the present invention relates to a gas turbine combustor.
- Combustion chambers in particular for gas turbines, are generally provided in their interior with a flow guide body, which is referred to as a liner.
- a combustible fluid mixture is supplied, which ignites in the combustion chamber of the combustion chamber and is passed through the liner in the direction of the outlet opening. Since the walls of the combustion chamber are exposed to high thermal loads due to the combustion taking place inside the combustion chamber, these parts of the combustion chamber must be cooled.
- a thermal barrier coating (ther ⁇ mal barrier coating) on the inside of the liner is usually not sufficient. Cooling is achieved, for example, by gaps ⁇ spaces through which a coolant is passed, which cools the combustion chamber convectively.
- the liner represents the transition to the turbine chamber and, for this reason, is conically shaped.
- the kuh ⁇ lung system must absorb the axial and radial thermal expansion of the liner with cone and ensure that even under changing conditions only a certain, defined amount of air ⁇ flows along the cone.
- Figure 1 shows a gas turbine combustor with convective cooling of the liner cone with an outer shell.
- the object of the invention is to provide a gas turbine combustor with improved cooling.
- a gas turbine combustor comprising an inner wall with cooling air holes and an outer wall spaced from the inner wall, the outer wall also has cooling air bores and is formed of a plurality of wall elements substantially juxtaposed in the circumferential direction of the gas turbine combustor and having a fixed bearing on a narrow side and are arranged with a movable bearing on an opposite narrow side on the inner wall, so that a cavity is formed between the two walls, the cooling of the liner cone can take place via an ef ⁇ fective baffle cooling.
- the wall elements are arranged on the burner side with a fixed bearing and the turbine side with ei ⁇ nem movable bearing on the inner wall.
- the inner wall prefferably has the shape of a hollow truncated cone and the wall elements to have the shape of hollow truncated segments.
- the loose bearing for easier assembly of ring segments, which have a groove for receiving a respective narrow side of the wall elements.
- the fixed bearing consists of Ringsegmen ⁇ th.
- At least one of the bearings has cooling air holes.
- brackets are provided in the region of an overlap of two wall elements each. It may be useful if the brackets are mounted on the inner wall.
- the Wandele- elements have openings for the supports, wherein the opening are ⁇ diameter greater than the diameter of the holders in this area.
- spacer elements In order to prevent that the wall elements of the outer wall up due to thermal deformation of the cone of the inner wall touch spacer elements (pins) between the inner and externa ⁇ ßerer wall arranged.
- These spacer elements are —waveßi ⁇ gate a central region of each wall element in relation to, that is disposed at the center among the wall elements, on the inner wall, for example welded.
- An embodiment of the ge ⁇ formed by the inner and the outer wall of the cavity as an acoustic damper (resonator) is particularly advantageous because the number of otherwise-required resonators can be reduced. This reduces ei ⁇ neix costs and saves the other hand, air that would be required for flushing or cooling of these resonators otherwise.
- FIG. 1 shows a gas turbine combustion chamber with a burner liner according to the prior art with external envelope for convective cooling
- FIG. 2 shows a gas turbine combustor according to the invention with wall elements for impingement cooling
- FIG. 3 shows a wall element with cooling-air bores and openings for fastening
- FIG. 4 a detail of a fixed bearing ring segment
- FIG. 5 shows a section through a burner liner of a gas turbine combustor according to the invention with a fixed bearing
- FIG. 6 shows a section through a burner liner of a gas turbine combustion chamber according to the invention with floating bearing
- FIG. 7 shows a plan view of a ring segment of the movable bearing
- FIG. 8 shows a gas turbine combustion chamber according to the invention without wall elements
- FIG. 10 shows a bolt in the installed state with conversion elements
- FIG. 1 shows schematically and exemplarily a Gasturbi ⁇ nenbrennhunt 1 according to the prior art with an inner wall 2 (Brenner liner), which surrounds the combustion chamber 3 and the combustion chamber side has a heat shielding layer 4, and an inner wall 2 surrounding envelope 5 between which cooling air 6 for convective cooling of the inner wall 2 is performed.
- the gas turbine combustor 1 In the transition from the combustion chamber 3 to the turbine chamber (not shown) are the gas turbine combustor 1 and thus the inner
- FIG. 1 shows a gas turbine combustor 8 according to the invention with an inner wall 2 and an outer wall 9 spaced therefrom, forming a cavity 10 (see Figures 5 and 6).
- the outer wall 9 is formed by a sheet metal construction, consisting of 8 wall elements 11, which can compensate for thermal expansions of the liner cone 7. A deviating from the embodiment of Figure 2 number of wall ⁇ elements 11 is possible.
- the wall elements 11 are welded on the burner-facing side 12 of the liner cone 7, ie to the truncated cone base, with the inner wall 2 and floating on the turbinenzugewand ⁇ th page 13 of the liner cone 7, ie the Kegelstumpfdeckflä ⁇ che out.
- a reverse solution is also possible.
- two rows of sheets 14, 15 are installed offset one above the other.
- the wall elements 11 For baffle cooling of the inner cone-shaped wall 2, the wall elements 11 have cooling air bores 16. Corresponding cooling air bores 17 are provided in the inner wall 2 (see FIGS 8 and 10), so that the air used for the impingement cooling can flow into the combustion chamber 3.
- FIG 3 shows a wall element 11 with cooling air holes 16.
- the wall elements 11 have for this purpose on two opposite narrow sides 19 openings 20, whose diameter is larger than the support diameter in this area, to ensure enough clearance for thermal expansion here.
- the two other narrow sides 21 together with the ring segments 22, 23 shown in FIGS. 4 to 7 form a fixed bearing and a movable bearing 24, 25.
- Figure 4 shows a section of a fixed bearing 24, insbeson ⁇ particular a ring segment 22 of a fixed bearing 24. If the Ring segment 22 welded to the inner wall 2 (see Figure 5), a cavity 26 is formed, which can be cooled via cooling air holes 27.
- Figure 5 shows a section through a fixed bearing 24 of a gas turbine combustor 8 according to the invention with a arranged on the burner liner 2 and connected thereto at the welds 28 ring segment 22 for the fixed bearing 24 and offset in the axial direction of the combustion chamber 8 arranged wall elements 11. Die Wandimplantation 11 are connected to the Ringseg ⁇ ment 22 at the welds 29. For assembly reasons, adjacent wall elements 11 in the axial direction ver ⁇ sets with the ring segments 22 welded.
- Figure 6 shows a section through a floating bearing 25 of a gas turbine combustor 8 according to the invention with a arranged on the burner liner 2 and connected thereto at the welds 30 ring segment 23 for the floating bearing 25.
- the ring segment 23 of the movable bearing 25 includes a groove 31 for receiving a Narrow side 21 of the wall elements 11 and lies directly on the inner wall 2, so that no cooling air holes in the ring segment 23 are necessary.
- Figure 7 shows a ring segment 23 for the floating bearing 25.
- the groove 31 for the floating support of the wall elements 11 in the ring ⁇ segment 23 extends according to the overlapping arrangement of the wall elements 11 at different radii with overlapping areas
- 32nd Figure 8 shows a gas turbine combustor 8 after the This sees both bolts 33 as parts of the brackets 18 against gape and other spacers or pins 34 angeord ⁇ net on the inner wall 2, which prevent the wall elements 11, the cone of the inner wall 2 due to thermal deformation touch.
- the pins 34 are typically welded in the middle under the wall ⁇ elements 11 on the inner wall 2.
- FIG. 9 shows a bolt 33 with a further mold element for easier mounting on the inner wall 2.
- the bolt 33 is part of a holder 18, as used against gaps between two adjacent wall elements 11.
- FIG. 10 shows such a holder 18 in the installed state. It is welded to the inner wall 2 and, where appropriate, ⁇ on the inner wall 2 in a provided recess 35 is arranged. In the area of the openings 21 of the wall elements 11, the bolt 33 of the holder 18 has a smaller diameter than the openings 21 itself, so that sufficient space for thermal expansions is present.
- the wall elements 11 are secured with a welded perforated disc 36, so that substantially only axial displacements of the wall elements 11 and displacements in the circumferential direction of the gas turbine combustor 8, but no radial movements are possible.
- FIG. 11 shows a plan view of the region of the holder 18.
- the invention is not limited to a conical geometry.
- the function of the device according to the invention is not limited to a cooling effect to be achieved, but can also be used as a resonance absorber.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102012213637.1A DE102012213637A1 (en) | 2012-08-02 | 2012-08-02 | combustion chamber cooling |
PCT/EP2013/062148 WO2014019754A1 (en) | 2012-08-02 | 2013-06-12 | Combustion chamber cooling |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2864705A1 true EP2864705A1 (en) | 2015-04-29 |
EP2864705B1 EP2864705B1 (en) | 2016-08-24 |
Family
ID=48652044
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP13729685.1A Not-in-force EP2864705B1 (en) | 2012-08-02 | 2013-06-12 | Combustion chamber cooling |
Country Status (6)
Country | Link |
---|---|
US (1) | US20150167978A1 (en) |
EP (1) | EP2864705B1 (en) |
CN (1) | CN104471316B (en) |
DE (1) | DE102012213637A1 (en) |
RU (1) | RU2015106899A (en) |
WO (1) | WO2014019754A1 (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN110822474B (en) * | 2019-11-06 | 2020-08-14 | 中国科学院工程热物理研究所 | Flame stabilizing structure of combustion chamber |
Family Cites Families (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4614082A (en) * | 1972-12-19 | 1986-09-30 | General Electric Company | Combustion chamber construction |
US4567730A (en) * | 1983-10-03 | 1986-02-04 | General Electric Company | Shielded combustor |
EP0224817B1 (en) * | 1985-12-02 | 1989-07-12 | Siemens Aktiengesellschaft | Heat shield arrangement, especially for the structural components of a gas turbine plant |
FR2723177B1 (en) * | 1994-07-27 | 1996-09-06 | Snecma | COMBUSTION CHAMBER COMPRISING A DOUBLE WALL |
FR2752916B1 (en) * | 1996-09-05 | 1998-10-02 | Snecma | THERMAL PROTECTIVE SHIRT FOR TURBOREACTOR COMBUSTION CHAMBER |
US6530221B1 (en) * | 2000-09-21 | 2003-03-11 | Siemens Westinghouse Power Corporation | Modular resonators for suppressing combustion instabilities in gas turbine power plants |
JP3962554B2 (en) * | 2001-04-19 | 2007-08-22 | 三菱重工業株式会社 | Gas turbine combustor and gas turbine |
US6931855B2 (en) * | 2003-05-12 | 2005-08-23 | Siemens Westinghouse Power Corporation | Attachment system for coupling combustor liners to a carrier of a turbine combustor |
US7146815B2 (en) * | 2003-07-31 | 2006-12-12 | United Technologies Corporation | Combustor |
US7363763B2 (en) * | 2003-10-23 | 2008-04-29 | United Technologies Corporation | Combustor |
US8146364B2 (en) * | 2007-09-14 | 2012-04-03 | Siemens Energy, Inc. | Non-rectangular resonator devices providing enhanced liner cooling for combustion chamber |
US20090120093A1 (en) * | 2007-09-28 | 2009-05-14 | General Electric Company | Turbulated aft-end liner assembly and cooling method |
DE102007062699A1 (en) * | 2007-12-27 | 2009-07-02 | Rolls-Royce Deutschland Ltd & Co Kg | combustion liner |
US20100095679A1 (en) * | 2008-10-22 | 2010-04-22 | Honeywell International Inc. | Dual wall structure for use in a combustor of a gas turbine engine |
US8051662B2 (en) * | 2009-02-10 | 2011-11-08 | United Technologies Corp. | Transition duct assemblies and gas turbine engine systems involving such assemblies |
US8413443B2 (en) * | 2009-12-15 | 2013-04-09 | Siemens Energy, Inc. | Flow control through a resonator system of gas turbine combustor |
-
2012
- 2012-08-02 DE DE102012213637.1A patent/DE102012213637A1/en not_active Ceased
-
2013
- 2013-06-12 EP EP13729685.1A patent/EP2864705B1/en not_active Not-in-force
- 2013-06-12 CN CN201380037779.8A patent/CN104471316B/en not_active Expired - Fee Related
- 2013-06-12 WO PCT/EP2013/062148 patent/WO2014019754A1/en active Application Filing
- 2013-06-12 RU RU2015106899A patent/RU2015106899A/en not_active Application Discontinuation
- 2013-06-12 US US14/417,945 patent/US20150167978A1/en not_active Abandoned
Non-Patent Citations (1)
Title |
---|
See references of WO2014019754A1 * |
Also Published As
Publication number | Publication date |
---|---|
DE102012213637A1 (en) | 2014-02-06 |
EP2864705B1 (en) | 2016-08-24 |
CN104471316A (en) | 2015-03-25 |
WO2014019754A1 (en) | 2014-02-06 |
US20150167978A1 (en) | 2015-06-18 |
RU2015106899A (en) | 2016-09-20 |
CN104471316B (en) | 2016-06-08 |
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