EP1818612B1 - Chambre de combustion annulaire d'une turbomachine - Google Patents
Chambre de combustion annulaire d'une turbomachine Download PDFInfo
- Publication number
- EP1818612B1 EP1818612B1 EP07102014A EP07102014A EP1818612B1 EP 1818612 B1 EP1818612 B1 EP 1818612B1 EP 07102014 A EP07102014 A EP 07102014A EP 07102014 A EP07102014 A EP 07102014A EP 1818612 B1 EP1818612 B1 EP 1818612B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- combustion chamber
- chamber
- sectors
- sector
- turbomachine
- 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.)
- Active
Links
- 238000002485 combustion reaction Methods 0.000 title claims description 39
- 238000011144 upstream manufacturing Methods 0.000 claims description 8
- 229910052751 metal Inorganic materials 0.000 claims description 6
- 239000002184 metal Substances 0.000 claims description 6
- 239000011153 ceramic matrix composite Substances 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 3
- 238000001816 cooling Methods 0.000 description 13
- 238000002347 injection Methods 0.000 description 11
- 239000007924 injection Substances 0.000 description 11
- 229910001092 metal group alloy Inorganic materials 0.000 description 6
- 229910010293 ceramic material Inorganic materials 0.000 description 5
- 239000000243 solution Substances 0.000 description 5
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 2
- 229910002091 carbon monoxide Inorganic materials 0.000 description 2
- 238000009792 diffusion process Methods 0.000 description 2
- 239000003344 environmental pollutant Substances 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000007800 oxidant agent Substances 0.000 description 2
- 230000001590 oxidative effect Effects 0.000 description 2
- 231100000719 pollutant Toxicity 0.000 description 2
- 230000000930 thermomechanical effect Effects 0.000 description 2
- 240000008042 Zea mays Species 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 238000004026 adhesive bonding Methods 0.000 description 1
- 238000012550 audit Methods 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 235000021183 entrée Nutrition 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 238000000638 solvent extraction Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
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
- F23R3/002—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
- F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
-
- 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
- F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
-
- 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
- F23R2900/00005—Preventing fatigue failures or reducing mechanical stress in gas turbine components
Definitions
- the invention relates to an annular combustion chamber of a turbomachine, of the type comprising an inner wall, an outer wall, a chamber bottom disposed between said walls in the upstream region of said chamber, and two fastening flanges arranged downstream. of the chamber bottom and for attaching respectively said walls to other parts of the turbomachine, usually inner and outer casings surrounding the combustion chamber.
- said inner and outer walls of the chamber were made of metal or metal alloy and it was necessary to cool these walls so that they can withstand the temperatures reached during operation of the turbomachine.
- Ceramic materials are more resistant to high temperatures and have a lower density than commonly used metals.
- the gains made in cooling air and in mass make it possible to improve the efficiency of the turbomachine.
- the ceramic materials used are preferably ceramic matrix composite materials chosen for their good mechanical properties.
- the state of the art leads to making these pieces of metal or metal alloy, rather than ceramic material, in order to be able to use the known fastening methods and tested to date, to fix the attachment flanges to the metal casings of the combustion chamber and the injection systems at the bottom of the chamber. It may be, for example, fasteners by welding or bolting.
- the ceramics used to make the walls often have a coefficient of expansion about three times less than that of the metal materials used to make the chamber bottom and said flanges.
- Such a gap generates stresses in the assembled parts during their assembly, as well as during the temperature rise thereof during operation. These stresses can be the cause of cracking in the fastening flanges or in the walls, if these flanges are not sufficiently flexible, the ceramic materials being by nature quite fragile.
- a solution described in the document FR 2,855,249 consists in providing a plurality of flexible fastening tabs connecting the chamber bottom audites walls, these tabs being able to deform elastically depending on the expansion gap between these parts.
- FR 2,825,781 and FR 2,825,784 consisting of connecting the walls to the casings of the combustion chamber by a plurality of flexible fasteners, elastically deformable, replacing the annular attachment flanges.
- the inner and outer walls of the combustion chamber are made in one piece of generally frustoconical shape.
- FR 2,855,249 there are spaces between the fastening tabs at the bottom of the chamber in which the fresh air rushes, which can degrade the efficiency of the combustion chamber by promoting the formation of pollutant emissions, such as for example, unburnt and / or carbon monoxide.
- the annular combustion chamber of the aforementioned type is such that each wall of the chamber is divided into several adjacent sectors, each sector being attached to the bottom of the chamber and to one of the snap flanges.
- the walls Thanks to the partitioning of the walls, they can deform depending on the expansion of the chamber bottom and the attachment flanges (this expansion being greater than that of the walls). For example, during a rise in temperature, during which the chamber bottom and / or The attachment flanges expand (ie their diameters increase), the adjacent sectors of the walls deviate circumferentially so that the diameters of these walls increase. This avoids the creation of thermomechanical stresses in these parts.
- the sectors of the walls are provided with side edges and the side edges of two adjacent sectors overlap, so as to limit the passage of fresh air between the sectors, from the outside to the inside of the combustion chamber. Indeed, such an air passage, if it is not controlled, causes the introduction of too much air into the chamber, which causes the formation of pollutant emissions such as, for example, unburned and carbon monoxide, and thus reduces the efficiency of the chamber. On the other hand, this passage of air, if it is controlled, can serve for the cooling of the walls, as explained hereafter.
- a known solution is to make a multitude of small perforations in said walls, through which calibrated volumes of fresh air pass. We usually talk about multiperforations. This solution nevertheless has the disadvantage of significantly increasing the cost price of said walls and cause a significant decrease in the characteristics of behavior and mechanical damage.
- This objective is achieved thanks to the fact that there is a radial clearance (ie in a direction perpendicular to the axis at the axis of rotation of the turbomachine) between two overlapping adjacent sectors, this clearance allowing the passage of air cool from the outside to the inside of said chamber to cool the inner face of at least one of the sectors.
- the fresh air coming from the outside of the chamber does not penetrate radially inside the chamber since the sectors overlap: it penetrates circumferentially while skirting, at least in part, the inner face of the chambers. inner and outer walls, so as to cool them.
- it controls the amount of cooling air entering the chamber.
- the invention aims to increase the cooling efficiency of the inner faces of the inner and outer walls.
- the lateral edges of the sectors are inclined circumferentially relative to the main axis of the combustion chamber, this main axis corresponding to the axis of rotation of the turbomachine.
- the circumferential direction at a point on the surface of a wall of the chamber is defined as the direction of the tangent to the wall, at this point, in a plane perpendicular to the axis of rotation. of the turbomachine.
- a lateral sectoral edge is inclined circumferentially with respect to the axis of rotation of the turbomachine, when this edge is inclined with respect to a generator of the wall concerned.
- the wall sectors are not attached to the chamber bottom and to the attachment flanges by means of flexible fasteners but, on the contrary, they are rigidly attached to these elements, for example by bolting.
- the structure has a better dynamic behavior in operation than a structure with flexible fastening tabs.
- the chamber bottom 30 and the attachment flanges 27 and 29 are made of metal alloy, while the walls 26 and 28 of the chamber 24 are made of ceramic matrix composite material.
- the walls 26 and 28 are respectively divided into several adjacent sectors 126 and 128.
- Each sector 126 (128) is attached to the chamber bottom 30, on the one hand, and to one of the attachment flanges 27 (29), on the other hand. At least one of these sectors may have multiperforations.
- each wall sector 126 (128) is attached to the bottom of the chamber. 30 or one of the attachment flanges 27 (29) at two points of attachment, at least.
- each sector 126 (128) is prevented from pivoting relative to the chamber bottom and / or said flange, thereby preventing the angular displacement of the chamber floor 30.
- each sector 126 (128) is attached at the bottom of the chamber 30 and at an attachment flange 27 (29) at two attachment points 36 and 36 '.
- At least one of these two attachment points 36 ' is made by bolting, by passing a bolt 52, through at least one oblong hole 50.
- This oblong hole 50 can be formed in the flap 32 (34). of the chamber bottom 30, in the sector 126 (128) or in these two pieces at a time.
- This oblong hole 50 is circumferentially oriented and the bolt 52 can therefore move circumferentially, inside the hole 50 as indicated by the double arrow B on the figure 4 .
- Each sector 128 (126) includes a lip 60 extending along one of its side edges 128a (126a), preferably substantially the entire length thereof.
- the other side edge of the sector is devoid of lip and will be hereinafter referred to as simple edge 128b (126b).
- the lip 60 projects from one of the inner or outer faces of the sector 128 (126) so as to cover the single edge 128b (126b) of the adjacent sector.
- the lip 60 is offset radially inwards or outwards with respect to the sector 128.
- the lip 60 is projecting (outwardly) relative to the outer face of the sector 128.
- it could be projecting (inwards) relative to the inner face of the sector.
- the outer and inner faces 126, 128 being turned respectively outwardly and inwardly of the combustion chamber 24.
- the lip 60 may be made directly during the manufacture of sector 128 (126), or during a subsequent machining step in its manufacture.
- the lip 60 may also consist of an added band, for example by gluing, on the lateral edge 128a (126a) of the sector.
- the fresh air circulates outside the chamber 24 according to the arrows F represented on the figure 1 , that is to say in a direction more axial than radial.
- the clearance J and the slot 66 form a passage which deviates little enough the flow of fresh air F 'entering the combustion chamber 24.
- this air flow F' remains sufficiently inclined relative to the radial direction as represented on the figures 1 and 4 to, on the one hand, disturb as little as possible the combustion inside the chamber 24 and, on the other hand, create a protective film of fresh air along the inner face of the wall segments 126, 128, which makes it possible to limit the heating of these segments.
- the side edges 126a, 126b, 128a, 128b of the sectors 126, 128 are inclined circumferentially with respect to the main axis of the combustion chamber. As indicated above, this circumferential inclination corresponds to an angle inclination y of the lateral edges relative to the generatrices G of the walls 126, 128.
- Tilting the side edges 126a, 126b, 128a, 128b and therefore the slots 66 for fresh air inlet allows to distribute the flow of fresh air F 'entering the chamber 24 in a cooling zone Z plus important that if said lateral edges were oriented along a generatrix G.
- This cooling zone Z is hatched on the figure 2 . The more the lateral edges 126, 128 are inclined, the more the zone Z is extended, and the better is the cooling of the wall sectors 126, 128.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Ceramic Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0650475A FR2897418B1 (fr) | 2006-02-10 | 2006-02-10 | Chambre de combustion annulaire d'une turbomachine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1818612A1 EP1818612A1 (fr) | 2007-08-15 |
EP1818612B1 true EP1818612B1 (fr) | 2010-09-29 |
Family
ID=37102414
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP07102014A Active EP1818612B1 (fr) | 2006-02-10 | 2007-02-09 | Chambre de combustion annulaire d'une turbomachine |
Country Status (7)
Country | Link |
---|---|
US (1) | US7788928B2 (ja) |
EP (1) | EP1818612B1 (ja) |
JP (1) | JP2007212129A (ja) |
CA (1) | CA2577520C (ja) |
DE (1) | DE602007009436D1 (ja) |
FR (1) | FR2897418B1 (ja) |
RU (1) | RU2429418C2 (ja) |
Families Citing this family (24)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2920525B1 (fr) * | 2007-08-31 | 2014-06-13 | Snecma | Separateur pour alimentation de l'air de refroidissement d'une turbine |
US8266914B2 (en) * | 2008-10-22 | 2012-09-18 | Pratt & Whitney Canada Corp. | Heat shield sealing for gas turbine engine combustor |
US10240790B2 (en) | 2013-11-04 | 2019-03-26 | United Technologies Corporation | Turbine engine combustor heat shield with multi-height rails |
EP3066390B1 (en) | 2013-11-04 | 2020-10-21 | United Technologies Corporation | Gas turbine engine wall assembly with offset rail |
EP3084310A4 (en) | 2013-12-19 | 2017-01-04 | United Technologies Corporation | Gas turbine engine wall assembly with circumferential rail stud architecture |
US10234140B2 (en) | 2013-12-31 | 2019-03-19 | United Technologies Corporation | Gas turbine engine wall assembly with enhanced flow architecture |
DE102014204482A1 (de) * | 2014-03-11 | 2015-09-17 | Rolls-Royce Deutschland Ltd & Co Kg | Brennkammer einer Gasturbine |
US9752447B2 (en) * | 2014-04-04 | 2017-09-05 | United Technologies Corporation | Angled rail holes |
US10648669B2 (en) | 2015-08-21 | 2020-05-12 | Rolls-Royce Corporation | Case and liner arrangement for a combustor |
US20170059159A1 (en) | 2015-08-25 | 2017-03-02 | Rolls-Royce Corporation | Cmc combustor shell with integral chutes |
FR3045137B1 (fr) * | 2015-12-11 | 2018-05-04 | Safran Aircraft Engines | Chambre de combustion de turbomachine |
US10473332B2 (en) | 2016-02-25 | 2019-11-12 | General Electric Company | Combustor assembly |
US10393380B2 (en) * | 2016-07-12 | 2019-08-27 | Rolls-Royce North American Technologies Inc. | Combustor cassette liner mounting assembly |
GB201613299D0 (en) | 2016-08-02 | 2016-09-14 | Rolls Royce Plc | A method of assembling an annular combustion chamber assembly |
US10670269B2 (en) | 2016-10-26 | 2020-06-02 | Raytheon Technologies Corporation | Cast combustor liner panel gating feature for a gas turbine engine combustor |
US10669939B2 (en) | 2016-10-26 | 2020-06-02 | Raytheon Technologies Corporation | Combustor seal for a gas turbine engine combustor |
US10830448B2 (en) | 2016-10-26 | 2020-11-10 | Raytheon Technologies Corporation | Combustor liner panel with a multiple of heat transfer augmentors for a gas turbine engine combustor |
US10823410B2 (en) | 2016-10-26 | 2020-11-03 | Raytheon Technologies Corporation | Cast combustor liner panel radius for gas turbine engine combustor |
US10935243B2 (en) | 2016-11-30 | 2021-03-02 | Raytheon Technologies Corporation | Regulated combustor liner panel for a gas turbine engine combustor |
CN106812556B (zh) * | 2017-03-16 | 2018-05-25 | 中国科学院工程热物理研究所 | 一种燃气轮机热端冷却结构及具有其的燃气轮机 |
US10598380B2 (en) * | 2017-09-21 | 2020-03-24 | General Electric Company | Canted combustor for gas turbine engine |
US11073285B2 (en) * | 2019-06-21 | 2021-07-27 | Raytheon Technologies Corporation | Combustor panel configuration with skewed side walls |
CN112902230A (zh) * | 2021-03-11 | 2021-06-04 | 西北工业大学 | 一种倾斜式入口双头部的双级旋流器燃烧室 |
US11747019B1 (en) * | 2022-09-02 | 2023-09-05 | General Electric Company | Aerodynamic combustor liner design for emissions reductions |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2544538A (en) * | 1948-12-01 | 1951-03-06 | Wright Aeronautical Corp | Liner for hot gas chambers |
US3854503A (en) * | 1971-08-05 | 1974-12-17 | Lucas Industries Ltd | Flame tubes |
US4543781A (en) * | 1981-06-17 | 1985-10-01 | Rice Ivan G | Annular combustor for gas turbine |
US5025622A (en) * | 1988-08-26 | 1991-06-25 | Sol-3- Resources, Inc. | Annular vortex combustor |
US5636508A (en) * | 1994-10-07 | 1997-06-10 | Solar Turbines Incorporated | Wedge edge ceramic combustor tile |
FR2825779B1 (fr) * | 2001-06-06 | 2003-08-29 | Snecma Moteurs | Chambre de combustion munie d'un systeme de fixation de fond de chambre |
FR2825781B1 (fr) | 2001-06-06 | 2004-02-06 | Snecma Moteurs | Montage elastique de chambre ce combustion cmc de turbomachine dans un carter metallique |
FR2825784B1 (fr) | 2001-06-06 | 2003-08-29 | Snecma Moteurs | Accrochage de chambre de combustion cmc de turbomachine utilisant les trous de dilution |
FR2855249B1 (fr) | 2003-05-20 | 2005-07-08 | Snecma Moteurs | Chambre de combustion ayant une liaison souple entre un fond de chambre et une paroi de chambre |
-
2006
- 2006-02-10 FR FR0650475A patent/FR2897418B1/fr active Active
-
2007
- 2007-02-08 CA CA2577520A patent/CA2577520C/fr active Active
- 2007-02-09 RU RU2007105075/06A patent/RU2429418C2/ru active
- 2007-02-09 EP EP07102014A patent/EP1818612B1/fr active Active
- 2007-02-09 DE DE602007009436T patent/DE602007009436D1/de active Active
- 2007-02-09 JP JP2007030344A patent/JP2007212129A/ja not_active Withdrawn
- 2007-02-09 US US11/673,179 patent/US7788928B2/en active Active
Also Published As
Publication number | Publication date |
---|---|
CA2577520A1 (fr) | 2007-08-10 |
CA2577520C (fr) | 2015-03-31 |
US7788928B2 (en) | 2010-09-07 |
RU2429418C2 (ru) | 2011-09-20 |
US20070186559A1 (en) | 2007-08-16 |
RU2007105075A (ru) | 2008-08-20 |
DE602007009436D1 (de) | 2010-11-11 |
JP2007212129A (ja) | 2007-08-23 |
FR2897418A1 (fr) | 2007-08-17 |
EP1818612A1 (fr) | 2007-08-15 |
FR2897418B1 (fr) | 2013-03-01 |
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