CN104471316A - Combustion chamber cooling - Google Patents
Combustion chamber cooling Download PDFInfo
- Publication number
- CN104471316A CN104471316A CN201380037779.8A CN201380037779A CN104471316A CN 104471316 A CN104471316 A CN 104471316A CN 201380037779 A CN201380037779 A CN 201380037779A CN 104471316 A CN104471316 A CN 104471316A
- Authority
- CN
- China
- Prior art keywords
- combustion chamber
- gas
- turbine combustion
- wall elements
- wall
- 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
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
The invention relates to a gas turbine combustion chamber (8), comprising an inner wall (2) having cooling air bores (17) and an outer wall (9) that is located at a distance from the inner wall (2), wherein the outer wall (9) likewise comprises cooling air bores (16) and is formed by a plurality of wall elements (11) that are arranged in the circumferential direction of the gas turbine combustion chamber (8) essentially next to each other, which wall elements are arranged on the inner wall (2) by means of a locating bearing (24) on a narrow side (21) and by means of a floating bearing (25) on an opposite narrow side (21), such that a hollow space (10) is formed between the two walls (2, 9).
Description
Technical field
The present invention relates to a kind of gas-turbine combustion chamber.
Background technology
The combustion chamber being particularly useful for gas turbine is provided with the baffle being called lining usually therein.By one or more burner be located in combustion chamber, input a kind of flammable fluid mixture, it lights in the combustion chamber of combustion chamber, and flows through lining and guide towards Way out.Because the wall of combustion chamber suffers high thermic load based on the burning carried out at combustion chamber, so these parts of combustion chamber must cool.Generally speaking, the thermal insulation layer (thermal barrier coating) inside lining is not enough to meet the demands.Cooling such as realizes by space, and cooling agent is directed through space, and it impels combustion chamber convection current cooling.
The variations in temperature occurred during owing to running, and make component produce thermal expansion.
Described lining becomes the transition region of leading to turbine chamber simultaneously, because this reason is designed to taper shape.Cooling system must bear the axial and radial thermal expansion of lining cone, and ensures, even if only flow through the air capacity of regulation along cone when condition transformation.
Fig. 1 represents the gas-turbine combustion chamber that a kind of lining cone convection current cools, and it has the overcoat in outside.
Summary of the invention
The technical problem to be solved in the present invention is, provides a kind of gas-turbine combustion chamber of better cooling.
By the present invention by solving the problems of the technologies described above according to gas-turbine combustion chamber according to claim 1.Determine the expansion design that the present invention is favourable in the dependent claims.Adopt a kind of gas-turbine combustion chamber for this reason, it comprises the inwall and the outer wall spaced apart with inwall with cooling air hole, wherein, outer wall has cooling air hole equally and is made up of multiple wall elements be substantially set up in parallel along gas-turbine combustion chamber circumference, the hold-down support that described wall elements is used in a narrow side and the floating support saddle being used in opposite narrow side are arranged on inwall, thus space is formed between two walls, in this gas-turbine combustion chamber, the cooling of lining cone realizes by effective impact type cooling.In addition, based on the temperature that matrix (about 900-1000 DEG C) is different from impinging cooling plate (about 500-600 DEG C), allowed the wall elements of impinging cooling plate effect relative to matrix, that is relative to the relative expansion of gas turbine inwall.
By a kind of favourable form of implementation, wall elements is arranged on inwall at burner side hold-down support and at turbo-side floating support saddle.
Here it is appropriate that inwall has the shape of hollow truncated cone body, and wall elements has the shape of hollow truncated cone body fan-shaped section.
In order to compensate thermal expansion radially better, adjacent wall elements overlap joint ground arrangement.
By a kind of favourable design, in order to assembling of being more convenient for, floating support saddle is made up of ring segment, and they have the groove for accepting a wall elements narrow side respectively.
It is appropriate that hold-down support is also made up of ring segment.
In order to cool bearing, one of at least described bearing has cooling air hole.
For avoiding adjacent wall elements to open, advantageously, in the overlap of every two wall elements, fixture is established.In this respect should it is appropriate that fixture be fixed on inwall.
In order to fixture also being made unstressed as far as possible when thermal expansion is different, wall elements has the hole of fixture, and the diameter in hole is greater than the diameter at this region inner fixing device.
In order to prevent the wall elements of outer wall based on the cone of thermal deformation contact inwall, spacing element is set between inwall and outer wall.These spacing elements worthily in the face of the center of respective wall elements, that is at center, below wall elements, are arranged on, such as, be welded on inwall.
Be muffler (resonator) by the void designs formed by inwall and outer wall be particularly advantageous, because can reduce thus otherwise the quantity of the resonator needed.Consequently, reduce costs on the one hand and save air on the other hand, generally needing air to rinse or cool these resonators.
The advantage of the technical scheme advised is, cools lining cone better by effective impinging cooling, and causes avoiding thermal stress by floating support saddle.In addition, by formed between lining cone and thin plate, the space of additionally playing resonator effect, damping intermediate frequency tremendously high frequency vibrates.
Accompanying drawing explanation
Exemplarily the present invention is elaborated below by accompanying drawing.Accompanying drawing schematically and does not represent by dimension scale ground:
Fig. 1 represents the gas-turbine combustion chamber by prior art, it there is combustor liner and in outside for the overcoat that convection current cools;
Fig. 2 represents that, by gas-turbine combustion chamber of the present invention, it has the wall elements for impinging cooling;
Fig. 3 represents wall elements, and it has cooling air hole and fixing hole;
Fig. 4 represents a part for hold-down support ring segment;
Fig. 5 represents by cutting by the combustor liner of gas-turbine combustion chamber of the present invention and hold-down support the profile illustrated open;
Fig. 6 represents by cutting by the combustor liner of gas-turbine combustion chamber of the present invention and floating support saddle the profile illustrated open;
Fig. 7 represents the top view of the ring segment of floating support saddle;
Fig. 8 represents by gas-turbine combustion chamber of the present invention, does not represent wall elements;
Fig. 9 represents the pin preventing opening of fixation wall element;
Figure 10 represents the pin and wall elements that are in loading state; And
Figure 11 represents the wall elements of overlap joint.
Detailed description of the invention
The gas-turbine combustion chamber 1 of prior art is pressed in Fig. 1 signal and exemplary expression, comprise around combustion chamber 3 and the inwall 2 (combustor liner) in combustion chamber side with thermal insulation layer 4, and around the overcoat 5 of inwall 2, be directed through the cooling-air 6 for convection current cooled inner wall 2 between which.From combustion chamber 3 to the transition region of turbine chamber (do not have represent), thus gas-turbine combustion chamber 1 also also has inwall 2 or combustor liner 2 to be configured as taper shape.Therefore this region is also referred to as lining cone 7.
Fig. 2 represents by gas-turbine combustion chamber 8 of the present invention, and it has inwall 2 and outer wall 9 separated by a distance with it, and they form space 10 (see Fig. 5 and Fig. 6).An outer ancient piece of jade, round, flat and with a hole in its centre 9 is consisted of the thin-slab structure be made up of 8 wall elements 11, and they can compensate the thermal expansion of lining cone 7.Allow the wall elements 11 different from quantity embodiment illustrated in fig. 2.
Wall elements 11 in that side 12 facing burner of lining cone 7, that is towards direction, truncated cone bottom surface, welds with inwall 2, and in that side 13 facing turbine of lining cone 7, that is towards truncated cone end face direction, floating ground supports.But contrary scheme is feasible equally.
Here two thin plate series 14, about 15 are installed with staggering.In order to impact type cooling cone shape inwall 2, wall elements 11 has cooling air hole 16.Inwall 2 arranges corresponding cooling air hole 17 (see Fig. 8 and Figure 10), and the air being used in impinging cooling can be flowed in combustion chamber 3 by them.
Fig. 3 represents the wall elements 11 with cooling air hole 16, can form gap at run duration between the wall elements 11 of overlap joint, and air will be arrived below thin-slab structure by this gap uncontrollably.But this gap is avoided by fixture 18 (see Figure 10,11).Wall elements 11 is two opposite narrow sides 19 porose 20 for this purpose, and their diameter is larger than the diameter at this region inner fixing device, in order that here also can ensure enough for the gap of thermal expansion.Two other narrow side 21 forms fixing and floating support saddle 24,25 jointly with the ring segment 22,23 represented in Fig. 4 to Fig. 7.
Fig. 4 represents a part for hold-down support 24, especially the part ring segment 22 of hold-down support 24.If ring segment 22 welds (see Fig. 5) with inwall 2, then form cavity 26, it can be cooled by cooling air hole 27.
Fig. 5 represents by cutting by the hold-down support 24 of gas-turbine combustion chamber 8 of the present invention the profile illustrated open, comprise and be arranged on the ring segment 22 for hold-down support 24 that is on combustor liner 2 and that be attached thereto in welding position 28, and the wall elements 11 be axially staggeredly arranged along combustion chamber 8.Wall elements 11 is connected with ring segment 22 in welding position 29.Due to assembling, adjacent wall elements 11 welds with ring segment 22 with staggering vertically.
Fig. 6 represents by cutting by the floating support saddle 25 of gas-turbine combustion chamber 8 of the present invention the profile illustrated open, comprises and is arranged on the ring segment 23 for floating support saddle 25 that is on combustor liner 2 and that be attached thereto in welding position 30.The ring segment 23 of floating support saddle 25 comprises the groove 31 for accepting the narrow side 21 of wall elements 11, and directly rests on inwall 2, so also do not need cooling air hole in ring segment 23.
Fig. 7 represents the ring segment 23 for floating support saddle 25.For the groove 31 of floating support wall elements 11 in ring segment 23, configure correspondingly with the overlap joint of wall elements 11, extended on different radii by Ta Jie district 32.
Fig. 8 represents and does not represent wall elements 11 by gas-turbine combustion chamber 8, figure of the present invention.Not only can see the pin 33 as fixture 18 part preventing from opening thus, but also can see other spacing elements or pin 34 of arranging on inwall 2, they prevent wall elements 11 due to the cone of thermal deformation contact inwall 2.Pin 34, typically at center, is welded on inwall 2 below wall elements 11.
Fig. 9 represents pin 3, has a larger shaped portion for the ease of being assemblied on inwall 2 it.Pin 3 is parts of fixture 18, uses fixture 18 to prevent opening between two adjacent wall elements 11.
Figure 10 represents this fixture 18 being in loading state.It welds with inwall 2 and is arranged on inwall 2 where necessary in for this reason set groove 35.On wall elements 11 hole 21 region in, the pin 3 of fixture 18 has than the little diameter in hole 21 itself, there is enough positions thus for thermal expansion.Wall elements 11 orifice plate 36 of burn-oning insures, so substantially only allow wall elements 11 to move axially and circumference along gas-turbine combustion chamber 8 moves, but can not radially move.Figure 11 represents the top view of fixture 18 region.
Although describe a kind of gas-turbine combustion chamber having cone lining in an embodiment, the present invention is not limited to conical geometry.In addition, be not limited to the cooling effect that will reach by the function of equipment of the present invention, but also can also be used in as resonance absorbing device.
Claims (13)
1. a gas-turbine combustion chamber (8), comprise the inwall (2) and the outer wall (9) spaced apart with described inwall (2) with cooling air hole (17), it is characterized by: outer wall (9) has cooling air hole (16) equally, and be made up of multiple wall elements (11) be substantially set up in parallel along gas-turbine combustion chamber (8) circumference, described wall elements is with the hold-down support (24) a narrow side (21) and to be arranged on described inwall (2) at the floating support saddle (25) of opposite narrow side (21), thus at two walls (2, 9) space (10) is formed between.
2. according to gas-turbine combustion chamber according to claim 1 (8), wherein, described wall elements (11) is arranged on described inwall (2) with floating support saddle (25) with hold-down support (24) and in turbo-side in burner side.
3. according to the gas-turbine combustion chamber (8) described in claim 1 or 2, wherein, described inwall (2) has the shape of hollow truncated cone body, and described wall elements (11) has the shape of hollow truncated cone body fan-shaped section.
4. according to the gas-turbine combustion chamber (8) one of all claims in prostatitis Suo Shu, wherein, adjacent wall elements (11) overlap joint ground arrangement.
5. according to the gas-turbine combustion chamber (8) one of all claims in prostatitis Suo Shu, wherein, floating support saddle (25) is made up of ring segment (23), described ring segment has the groove (31) for accepting wall elements (11) narrow sides (21) respectively.
6. according to the gas-turbine combustion chamber (8) one of all claims in prostatitis Suo Shu, wherein, described hold-down support (24) is made up of ring segment (22).
7. according to the gas-turbine combustion chamber (8) one of all claims in prostatitis Suo Shu, wherein, one of at least described bearing (24,25) has cooling air hole (27).
8. according to the gas-turbine combustion chamber (8) one of all claims in prostatitis Suo Shu, wherein, in the overlap (32) of every two wall elements (11), be provided with fixture (18), prevent these two wall elements (11) from opening.
9. according to gas-turbine combustion chamber according to claim 8 (8), wherein, described fixture (18) is fixed on described inwall (2).
10. according to the gas-turbine combustion chamber (8) one of claim 8 or 9 Suo Shu, wherein, described wall elements (11) has the hole (20) for fixture (18), and the diameter in hole is greater than the diameter at this region inner fixing device (18).
11. according to the gas-turbine combustion chamber (8) one of all claims in prostatitis Suo Shu, wherein, arranges spacing element (34) between described inwall (2) and outer wall (9).
12. according to gas-turbine combustion chamber according to claim 11 (8), and wherein, described spacing element (34) is arranged on described inwall (2) in the face of the center of respective wall elements (11).
13. according to the gas-turbine combustion chamber (8) one of all claims in prostatitis Suo Shu, and wherein, the space (10) formed between described inwall (2) and outer wall (9) is designed to muffler.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102012213637.1 | 2012-08-02 | ||
| 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 |
|---|---|
| CN104471316A true CN104471316A (en) | 2015-03-25 |
| CN104471316B CN104471316B (en) | 2016-06-08 |
Family
ID=48652044
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201380037779.8A Expired - Fee Related CN104471316B (en) | 2012-08-02 | 2013-06-12 | Combustor cools down |
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) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110822474A (en) * | 2019-11-06 | 2020-02-21 | 中国科学院工程热物理研究所 | Flame stabilizing structure of combustion chamber |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2009038611A2 (en) * | 2007-09-14 | 2009-03-26 | Siemens Energy, Inc. | Non-rectangular resonator devices providing enhanced liner cooling for combustion chamber |
| DE102007062699A1 (en) * | 2007-12-27 | 2009-07-02 | Rolls-Royce Deutschland Ltd & Co Kg | combustion liner |
| CN101514658A (en) * | 2007-09-28 | 2009-08-26 | 通用电气公司 | Rear end liner assembly with turbulator and its cooling method |
| US20100199677A1 (en) * | 2009-02-10 | 2010-08-12 | United Technologies Corp. | Transition Duct Assemblies and Gas Turbine Engine Systems Involving Such Assemblies |
Family Cites Families (12)
| 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 |
| US20100095679A1 (en) * | 2008-10-22 | 2010-04-22 | Honeywell International Inc. | Dual wall structure for use in a combustor of a gas turbine engine |
| 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 RU RU2015106899A patent/RU2015106899A/en not_active Application Discontinuation
- 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 US US14/417,945 patent/US20150167978A1/en not_active Abandoned
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2009038611A2 (en) * | 2007-09-14 | 2009-03-26 | Siemens Energy, Inc. | Non-rectangular resonator devices providing enhanced liner cooling for combustion chamber |
| CN101514658A (en) * | 2007-09-28 | 2009-08-26 | 通用电气公司 | Rear end liner assembly with turbulator and its cooling method |
| DE102007062699A1 (en) * | 2007-12-27 | 2009-07-02 | Rolls-Royce Deutschland Ltd & Co Kg | combustion liner |
| US20100199677A1 (en) * | 2009-02-10 | 2010-08-12 | United Technologies Corp. | Transition Duct Assemblies and Gas Turbine Engine Systems Involving Such Assemblies |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110822474A (en) * | 2019-11-06 | 2020-02-21 | 中国科学院工程热物理研究所 | Flame stabilizing structure of combustion chamber |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| RU2015106899A (en) | 2016-09-20 |
| EP2864705A1 (en) | 2015-04-29 |
| DE102012213637A1 (en) | 2014-02-06 |
| US20150167978A1 (en) | 2015-06-18 |
| EP2864705B1 (en) | 2016-08-24 |
| WO2014019754A1 (en) | 2014-02-06 |
| CN104471316B (en) | 2016-06-08 |
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| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160608 Termination date: 20180612 |
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| CF01 | Termination of patent right due to non-payment of annual fee |