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
  • 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
  • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
• • 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
• • 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
  • F23R3/10—Air inlet arrangements for primary air
• • 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
  • F23R2900/03041—Effusion cooled combustion chamber walls or domes
• • 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 present invention relates generally to the field of annular combustion chambers of a turbomachine, and more particularly to that of the means making it possible to thermally protect these combustion chambers.
• an annular combustion chamber of a turbomachine comprises an external axial wall and an internal axial wall, these walls being arranged coaxially and connected to each other via a chamber bottom.
• the combustion chamber is provided with angularly spaced injection orifices, each of them being intended to receive a fuel injector in order to allow combustion reactions to inside this combustion chamber. It is also noted that these injectors can also make it possible to introduce at least part of the air intended for combustion, the latter occurring in a primary zone of the combustion chamber, located upstream of a secondary zone. said dilution zone.
• deflectors are arranged on the chamber bottom, in order to protect it from thermal radiation.
• Each deflector also called a cup or heat shield, then has at least one injection orifice intended to receive a fuel injector, as well as a plurality of perforations making it possible to allow cooling air to pass inside the combustion chamber.
• the object of the invention is therefore to propose an annular combustion chamber for a turbomachine, at least partially remedying the drawbacks mentioned above relating to the embodiments of the prior art. More specifically, the object of the invention is to present an annular combustion chamber of turbomachine, the means of which used to cool the chamber bottom generate neither significant disturbance of the combustion reactions inside the combustion chamber, nor thermal discontinuities at the junctions between the chamber bottom and the external axial walls and internal.
• the invention relates to an annular combustion chamber of a turbomachine, comprising an external axial wall, an internal axial wall and a chamber bottom connecting the axial walls, the chamber bottom having a plurality of orifices injection as well as a plurality of perforations, the injection orifices being intended to allow at least the injection of fuel inside the combustion chamber and the perforations being intended to allow the passage of a flow cooling air capable of cooling the bottom of the chamber.
• the chamber bottom is provided on the one hand with an external portion on which the perforations are made so as to direct part of the cooling air flow in the direction of the external axial wall, and other part of an internal portion on which the perforations are formed so as to direct another part of the cooling air flow towards the internal axial wall, and the chamber is designed so that in axial half-section , taken in any way between two directly consecutive injection orifices, the value of the acute angles formed between a substantially median line of the half-section situated between the external axial wall and the axial wall internal, and of the main directions, in this half-section, of the perforations of the external portion, evolves in a decreasing fashion as a function of the distance between the perforations and this substantially median line, and the value of the acute angles formed between the substantially median and main directions, in this half-section, of the perforations of the internal portion, decreases as a function of the distance between the perforations and this substantially median line.
• the perforations located near the junction between the external portion and the internal portion of the chamber bottom can therefore be strongly inclined in the direction of the axial walls, and consequently allow the cooling air coming from these perforations of s '' flow easily and directly along the inner surface of the chamber bottom, substantially radially to the external and internal axial walls.
• this strong possible tilt indicates that the air from cooling is only very little directed towards the center of the primary zone of the combustion chamber, so that it does not cause a significant disturbance of the combustion reactions.
• the perforations located near the axial walls may be inclined only slightly towards these axial walls, so that the cooling air coming from these perforations can easily and directly flow along the surfaces interior of these same axial walls.
• the combustion chamber according to the invention is therefore perfectly adapted so as not to generate significant disturbance of the combustion reactions inside the primary zone, which is essential for the stability and ignition of the combustion chamber.
• the specific design of this chamber simultaneously ensures satisfactory thermal continuity at the junctions between the chamber bottom and the external and internal axial walls.
• the two acute angles formed between the main directions of these perforations and the substantially median line have different values
• the two acute angles formed between the main directions of these perforations and the substantially median line have different values
• FIG. 1 represents a partial view in axial half-section of an annular combustion chamber of a turbomachine, according to a preferred embodiment of the present invention
• annular combustion chamber 1 of a turbomachine With reference jointly to Figures 1 and 2, there is shown an annular combustion chamber 1 of a turbomachine, according to a preferred embodiment of the present invention.
• the combustion chamber 1 comprises an external axial wall 2, as well as an internal axial wall 4, these two walls 2 and 4 being arranged coaxially along a longitudinal main axis 6 of the chamber 1, this axis 6 also corresponding to the axis main longitudinal of the turbomachine.
• the axial walls 2 and 4 are interconnected by means of a chamber bottom 8, the latter being assembled for example by welding to an upstream part of each of the axial walls 2 and 4.
• the chamber bottom 8 preferably takes the form of a substantially planar annular ring, with an axis identical to the main longitudinal axis 6 of the chamber 1.
• this chamber wav 8 could also have any other suitable shape, such as a frustoconical shape of the same axis, without departing from the scope of the invention.
• Each of these injection orifices 10 is designed so as to be able to cooperate with a fuel injector 12, in order to allow the combustion reactions inside this combustion chamber 1.
• these injectors 12 are also designed to so as to allow the introduction of at least part of the air intended for combustion, the latter occurring in a primary zone 14 situated in an upstream part of the combustion chamber 1.
• the air intended for combustion can also be introduced inside the chamber 1 by means of primary orifices 16, situated all around the external axial 2 and internal 4 walls.
• the primary orifices 16 are arranged upstream of a plurality of dilution orifices 18, the latter also being placed all around the external axial 2 and internal 4 walls, and having the main function of allowing the supply of air d a dilution zone 20 located downstream of the primary zone 14.
• a cooling air flow D serving mainly to cool the interior surface 21 of the chamber bottom 8.
• an additional cooling air flow (not shown) is generally allocated to cool all of these hot interior surfaces 22 and 24.
• the bottom of the chamber 8 is of the ultra-perforated type, namely that it has a plurality of perforations 26, preferably cylindrical with circular sections, and intended to allow the passage of the cooling air flow D inside the combustion chamber 1.
• the chamber bottom 8 is divided into an external portion 28 connected to the external axial wall 2, and into an internal portion 30 connected to the internal axial wall.
• these annular portions 28 and 30 are usually formed in one piece, and their virtual separation can then consist of a circle C with a center located on the main longitudinal axis 6, and with radius R corresponding to an average radius between an outer radius and an inner radius of the chamber bottom 8.
• the perforations preferably cylindrical with circular sections
• the perforations 26 located on the internal portion 30 are formed so as to direct another part D2 of the cooling air flow D towards the internal axial wall 4, in order to cool the whole of this internal portion 30, as well as an upstream portion of the internal axial wall 4.
• the perforations 26 of the external portion 28 are such that the value of the acute angles A formed between a line substantially median 32 of the half-section and of the main directions 34 of the perforations 26 in this half-section, decreases as a function of the distance between these perforations 26 and this substantially median line 32.
• this substantially central line 32 passing through the circle C, is also substantially perpendicular to the chamber bottom 8, insofar as it itself is substantially perpendicular to the axial walls 2 and 4.
• the main directions 34 of the perforations 26 respectively correspond to their main axes, in the sense that these perforations 26 are all crossed diametrically by the section plane.
• each main direction 34 can then be considered to be a line substantially parallel to the two straight segments symbolizing the perforation 26 concerned.
• the perforations 26 located near the substantially central line 32 can therefore be strongly inclined, for example so that the acute angle A reaches a value of about 60 °.
• the cooling air coming from these perforations 26 can therefore flow easily and directly along the internal surface 21 of the external portion 28 of the chamber bottom 8, substantially radially up to the external axial wall 2, without disturbing combustion reactions in the primary zone 14.
• the perforations 26 located near the external axial wall 2 may be inclined only slightly towards this wall 2, for example so that the acute angle A reaches a value of approximately 5 °.
• the cooling air coming from these perforations 26 can then easily and directly flow along the hot internal surface 22 of the external axial wall 2, without stagnating at the junction between the chamber bottom 8 and this same wall. axial 2.
• the perforations 26 of the internal portion 30 are such that the value of the acute angles B formed between the substantially median line 32 and the main directions 36 of the perforations 26 in this half-section, decreases as a function of the distance between these perforations 26 and this substantially median line 32.
• the value of the acute angles B formed between on the one hand the main directions 36 of the perforations 26 of the internal portion 30, and on the other hand the line substantially median 32, can progressively evolve from approximately 60 ° to approximately 5 °, approaching the internal axial wall 4.
• the chamber bottom 8 is provided with primary sectors 38 of perforations 26, these primary sectors 38 being situated substantially between two directly consecutive injection orifices 10.
• at least part of the perforations 26 of each primary sector 38 are arranged so as to define rows taking the form of curved lines centered on the center of the injection orifice 10 near which these perforations 26 are located.
• the chamber bottom 8 is also provided with secondary sectors 40 of perforations 26, these secondary sectors 40 each lying between two consecutive primary sectors 38, on either side of an injection orifice 10 in a direction. substantially radial from the combustion chamber 1.
• a secondary sector 40 is located both above and below the injection orifice 10 concerned.
• the perforations 26 of the outer portion 28 are such that the value of the acute angles C formed between a substantially median line 42 of the half-section and the main directions 44 of the perforations 26 in this half-section, decreases as a function of the distance between these perforations 26 and this substantially median line 42.

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• Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Combustion Methods Of Internal-Combustion Engines (AREA)
• Fuel-Injection Apparatus (AREA)
• Turbine Rotor Nozzle Sealing (AREA)
• Cylinder Crankcases Of Internal Combustion Engines (AREA)

Applications Claiming Priority (2)

Publications (2)

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Family Applications (1)

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• 2003
  • 2003-06-18 FR FR0350232A patent/FR2856467B1/fr not_active Expired - Lifetime
• 2004
  • 2004-06-18 RU RU2005107793/06A patent/RU2351849C2/ru active
  • 2004-06-18 JP JP2006516352A patent/JP2006527834A/ja active Pending
  • 2004-06-18 KR KR1020057010887A patent/KR20060029203A/ko not_active Application Discontinuation
  • 2004-06-18 US US10/529,583 patent/US7328582B2/en active Active
  • 2004-06-18 WO PCT/FR2004/050281 patent/WO2004113794A1/fr active Application Filing
  • 2004-06-18 EP EP04767843.8A patent/EP1634021B1/de active Active
  • 2004-06-18 CN CNA2004800009068A patent/CN1701203A/zh active Pending

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