EP3289288A1 - Chambre de combustion coudée d'une turbomachine - Google Patents
Chambre de combustion coudée d'une turbomachineInfo
- Publication number
- EP3289288A1 EP3289288A1 EP16721468.3A EP16721468A EP3289288A1 EP 3289288 A1 EP3289288 A1 EP 3289288A1 EP 16721468 A EP16721468 A EP 16721468A EP 3289288 A1 EP3289288 A1 EP 3289288A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- flame tube
- injector
- chamber
- combustion chamber
- inlet
- 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
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 26
- 239000000446 fuel Substances 0.000 claims description 7
- 238000002347 injection Methods 0.000 claims description 7
- 239000007924 injection Substances 0.000 claims description 7
- 238000010790 dilution Methods 0.000 claims description 3
- 239000012895 dilution Substances 0.000 claims description 3
- 238000001816 cooling Methods 0.000 description 1
- 230000037406 food intake Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
-
- 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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
Definitions
- the invention relates to the field of combustion chambers for turbomachines and more particularly the structure and the fixing of a flame tube in a combustion chamber of a turbomachine.
- a turbomachine downstream of a high pressure compressor (not shown), a turbomachine comprises a combustion chamber delimited by inner and outer casings of revolution 1b that are concentric.
- the combustion chamber comprises a flame tube 2 disposed in the space defined by the inner casing 1a and outer 1b.
- the flame tube 2 is delimited by internal walls 2a and external 2b called internal and external ferrules and a bottom plate of chamber 3 which serves as support for injectors 4.
- the combustion chamber also comprises a shroud 5 arranged in front of the chamber floor to partially cover the injectors 4 and protect them from possible shocks (that can occur when ingestion of a bird or an ice block in engines).
- the combustion chamber comprises an air diffuser 6 opening on the injector 4.
- the bottom plate 3, the inner walls 2a and outer 2b of the flame tube 2 and the shroud 5 are assembled by bolts (not shown).
- the combustion chamber of FIG. 1 is called direct axial annular in that it extends in the preferred direction of the motor axis without turning cylindrical ferrules of the flame tube.
- This architecture is the reference for modern turbomachines, especially on high power. In the field of small powers, it coexists with the return chamber architecture which is very compact axially. However, it has the main drawback a large surface area to volume that makes it difficult to cool the walls of the flame tube and handicaps their lives.
- the invention proposes to overcome at least one of these disadvantages.
- a combustion chamber of a turbomachine comprising: an outer annular casing; a flame tube connected to the outer casing, said flame tube comprising an inner annular wall and an outer annular wall defining firstly a first radial portion at the inlet of the flame tube and secondly a second axial portion at the outlet of the flame tube, the first portion extending to the second portion forming a bend between the inlet and the outlet of the flame tube.
- the invention is advantageously completed by the following characteristics, taken alone or in any of their technically possible combination.
- the flame tube comprises a chamber bottom located at the inlet of the flame tube, the chamber comprising at least one fuel injector configured to inject fuel into the flame tube via the inlet of the flame tube, the flame tube being connected. to the outer casing via said injector in connection with the chamber bottom.
- the injector has a principal direction coaxial with a longitudinal axis Y in which the first portion extends.
- the injector comprises an injector body surrounding an injection pipe through which fuel is fed into the flame tube, the injector body being inserted into a cylinder surmounting a connecting disk connected to the chamber bottom.
- the inner and outer annular walls of the flame tube are connected to the outer casing via the injector body.
- the injector body is connected to the injection pipe, the injector body being movable relative to the cylinder.
- the chamber includes primary holes drilled in the inner and outer annular walls at the first portion and dilution holes drilled in the inner and outer annular walls at a bend of the flame tube.
- the invention relates to a turbomachine comprising a combustion chamber according to the invention.
- the invention greatly reduces the axial size of the combustion chamber. This has the following advantages,
- the shape of the flame tube makes it possible to reduce the length of the outer casing, which is often common with the high-pressure turbine downstream of the combustion chamber;
- the structure of the chamber is simplified in particular by the fact that the flame tube is connected to the outer casing via the injector which allows to remove the cowling and associated bolts. These parts are generally used on direct axial type chambers;
- the spark plug can be positioned at different positions: at the bottom of the chamber and / or in the chamber corner and / or on the outer wall.
- Figure 2 illustrates a sectional view of a combustion chamber
- Figure 3 illustrates a perspective view of a combustion chamber
- FIG. 4 illustrates a detailed view of the perspective view of FIG. 3.
- FIGS. 2 and 3 illustrate views of a combustion chamber according to one embodiment.
- the combustion chamber comprises an outer casing 10a to which is connected a flame tube 20.
- the flame tube 20 comprises an inner annular wall 20a and an outer annular wall 20b.
- the inner and outer annular walls define on the one hand a first portion
- the inner and outer annular walls define a second portion
- the first portion 201 extends to the second portion 202 forming a bend between the inlet and the outlet of the flame tube.
- Such a bend allows an effective aerodynamic connection with a high pressure stage downstream of the gas flow (dashed arrow in Figure 2).
- this bent shape makes it possible to reduce the axial size of the flame tube 20.
- the combustion chamber also comprises a chamber bottom 30 which has the shape of a plate located at the inlet of the flame tube 20.
- an injector 40 through which is connected the flame tube 20 to the outer casing 10a of the turbomachine.
- combustion chamber may optionally include a heat shield 50 in the form of a plate attached to the chamber bottom 30 located in the tube 20.
- This heat shield 50 is located at the entrance of the flame tube 20 and protects the injector 40 from high temperatures above 2200 K can prevail in the flame tube 20.
- Primary holes 202a, 202b are drilled in the inner and outer annular walls at the first portion 201 at the inlet of the flame tube.
- dilution holes 203a, 203b are drilled in the inner and outer annular walls at the bent portion of the flame tube 20 (see Figure 3).
- the number of holes, their respective diameters and positions may vary depending on the intended application.
- the injector 40 comprises an injector body 40a surrounding an injection pipe 40b through which the fuel is introduced as such into the flame tube 20.
- the injector body 40a is fixed to the outer casing 10a by means of bolts 70 and fixing plates 80 (see Figure 3).
- the inner and outer annular walls are fixed to the outer casing 10a via the injector body 40a thus making it possible to simplify the bowl-chamber connection and thus to avoid the use of a play-catching system.
- a connecting disk 40c surmounted by a cylinder 40d in which is inserted the body 40a of the injector is connected to the chamber bottom 30 in which a recess 30a to the size of the connecting disk has been formed.
- the body 40a of the injector is connected to the injection pipe 40b and the body 40a of the injector 40 is inserted into the cylinder 40d surmounting the connecting disc 40c so that the injector body 40a (and therefore the injection pipe 40b) is movable relative to the cylinder 40d. This allows a compensation of the movements to which the flame tube 20 is subjected. There is therefore no need for complex compensation systems.
- the body 40a of the injector comprises an air inlet 40e through which air from a diffuser 60 is introduced. This air is used to cool the injector 40.
- the air inlet 40e has the shape of an oval recess formed in the injector body 40a.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Fuel-Injection Apparatus (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1553876A FR3035707B1 (fr) | 2015-04-29 | 2015-04-29 | Chambre de combustion coudee d'une turbomachine |
PCT/FR2016/051004 WO2016174363A1 (fr) | 2015-04-29 | 2016-04-28 | Chambre de combustion coudée d'une turbomachine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3289288A1 true EP3289288A1 (fr) | 2018-03-07 |
EP3289288B1 EP3289288B1 (fr) | 2020-06-24 |
Family
ID=53524837
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP16721468.3A Active EP3289288B1 (fr) | 2015-04-29 | 2016-04-28 | Chambre de combustion coudée d'une turbomachine |
Country Status (5)
Country | Link |
---|---|
US (1) | US10883720B2 (fr) |
EP (1) | EP3289288B1 (fr) |
CN (1) | CN107532800B (fr) |
FR (1) | FR3035707B1 (fr) |
WO (1) | WO2016174363A1 (fr) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3038699B1 (fr) | 2015-07-08 | 2022-06-24 | Snecma | Chambre de combustion coudee d'une turbomachine |
Family Cites Families (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3088279A (en) * | 1960-08-26 | 1963-05-07 | Gen Electric | Radial flow gas turbine power plant |
GB2008199A (en) * | 1977-09-03 | 1979-05-31 | Lucas Industries Ltd | Flame Tube |
GB2097112B (en) * | 1981-04-16 | 1984-12-12 | Rolls Royce | Fuel burners and combustion equipment for use in gas turbine engines |
US4955201A (en) * | 1987-12-14 | 1990-09-11 | Sundstrand Corporation | Fuel injectors for turbine engines |
WO2007033306A2 (fr) * | 2005-09-13 | 2007-03-22 | Rolls-Royce Corporation, Ltd. | Systemes de combustion pour turbine a gaz |
FR2892180B1 (fr) * | 2005-10-18 | 2008-02-01 | Snecma Sa | Amelioration des perfomances d'une chambre de combustion par multiperforation des parois |
US7716931B2 (en) * | 2006-03-01 | 2010-05-18 | General Electric Company | Method and apparatus for assembling gas turbine engine |
US8096132B2 (en) * | 2008-02-20 | 2012-01-17 | Flexenergy Energy Systems, Inc. | Air-cooled swirlerhead |
US8297048B2 (en) * | 2008-10-02 | 2012-10-30 | Cummins Inc. | Apparatus and method for mounting a close-coupled catalyst |
US8141368B2 (en) * | 2008-11-11 | 2012-03-27 | Delavan Inc | Thermal management for fuel injectors |
FR2953907B1 (fr) * | 2009-12-11 | 2012-11-02 | Snecma | Chambre de combustion pour turbomachine |
WO2012156631A1 (fr) * | 2011-05-17 | 2012-11-22 | Snecma | Chambre annulaire de combustion pour une turbomachine |
US9388742B2 (en) * | 2013-05-08 | 2016-07-12 | Solar Turbines Incorporated | Pivoting swirler inlet valve plate |
US9592480B2 (en) * | 2013-05-13 | 2017-03-14 | Solar Turbines Incorporated | Inner premix tube air wipe |
US20170059163A1 (en) * | 2014-07-11 | 2017-03-02 | United Technologies Corporation | Additively manufactured swirler mount interface for gas turbine engine combustor |
FR3031799B1 (fr) * | 2015-01-19 | 2017-02-17 | Snecma | Dispositif d'etancheite ameliore entre un systeme d'injection et un nez d'injecteur de carburant de turbomachine d'aeronef |
US10095218B2 (en) * | 2016-08-03 | 2018-10-09 | Siemens Aktiengesellschaft | Method and computer-readable model for additively manufacturing ducting arrangement with injector assemblies forming a shielding flow of air |
US10422533B2 (en) * | 2017-01-20 | 2019-09-24 | General Electric Company | Combustor with axially staged fuel injector assembly |
-
2015
- 2015-04-29 FR FR1553876A patent/FR3035707B1/fr active Active
-
2016
- 2016-04-28 CN CN201680024416.4A patent/CN107532800B/zh active Active
- 2016-04-28 WO PCT/FR2016/051004 patent/WO2016174363A1/fr active Application Filing
- 2016-04-28 US US15/569,593 patent/US10883720B2/en active Active
- 2016-04-28 EP EP16721468.3A patent/EP3289288B1/fr active Active
Also Published As
Publication number | Publication date |
---|---|
CN107532800B (zh) | 2020-01-03 |
FR3035707A1 (fr) | 2016-11-04 |
US20180299132A1 (en) | 2018-10-18 |
CN107532800A (zh) | 2018-01-02 |
FR3035707B1 (fr) | 2019-11-01 |
US10883720B2 (en) | 2021-01-05 |
WO2016174363A1 (fr) | 2016-11-03 |
EP3289288B1 (fr) | 2020-06-24 |
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