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
  • 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
  • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
  • F23R3/26—Controlling the air flow
• • 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
  • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
  • F23R3/54—Reverse-flow combustion chambers
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2240/00—Components
  • F05D2240/35—Combustors or associated equipment

Definitions

• the present disclosure relates to an annular combustion chamber, and more particularly to an annular combustion chamber comprising a first annular wall and a second annular wall coaxial about an axis, a chamber base connecting the first and second walls, and a plurality of injectors, the first wall having first air supply holes downstream of the injectors.
• a combustion chamber may be a turbomachine combustion chamber.
• Combustion chambers of this type are known, for example EP 0 569 300 which describes a guillotine device for changing the axial position of a closure member of primary supply holes.
• EP 0 569 300 which describes a guillotine device for changing the axial position of a closure member of primary supply holes.
• At least a first of said injectors at least three, preferably at least four, first holes having in common the first injector as the nearest injector are located equidistant from the first injector.
• said first holes are arranged on a circular arc centered on the first injector.
• the arc of a circle is a curve which is strictly convex in radial view and, in this case, whose concavity is turned towards the first injector.
• the curve defines, in radial projection, a strictly convex surface, the injector being located in said surface.
• a convex surface is such that, whatever two points belonging to the convex surface, the line segment connecting these two points belongs wholly to said convex surface.
• a surface is strictly convex if the curve which delimits it contains no straight portion.
• the present disclosure proposes to dimension the position of the first holes relative to the injector closest to said holes. . This results in better control of the flow and the temperature field in the combustion chamber.
• the first injector and preferably all injectors, can be placed on the chamber bottom or on one of the annular walls, in particular on the first wall.
• the axis of the combustion chamber is called the axis of symmetry (or quasi-symmetry) of the combustion chamber.
• the axial direction corresponds to the direction of the axis of the combustion chamber and a radial direction is a direction perpendicular to the axis of the combustion chamber and intersecting this axis.
• an axial plane is a plane containing the axis of the combustion chamber and a radial plane is a plane perpendicular to this axis.
• a circumference is understood as a circle belonging to a radial plane and whose center belongs to the axis of the combustion chamber.
• a tangential or circumferential direction is a direction tangent to a circumference; it is perpendicular to the axis of the combustion chamber but does not pass through the axis.
• the first holes may be primary holes, i.e. holes configured to introduce fresh air, for example from the compressor, so as to delimit by turbulence, between the injectors and said holes, an anchoring zone of the flame to ensure its stability and good combustion. This zone is called primary zone.
• the first holes may be dilution holes, i.e. holes configured to introduce fresh air, e.g. from the compressor, into the heart of the combustion chamber, distance downstream of the flame of the injector.
• all the first holes having in common the same nearest injector are located equidistant from this injector.
• the first holes are positioned according to their distance from the nearest injector, which allows to control the recirculation zones and therefore the temperature field in the combustion chamber. .
• the second wall has second air supply holes downstream of the injectors.
• the second holes may be positioned similarly to the first holes, or in a different manner.
• the second holes preferably all the second holes, having in common the same nearest injector are located equidistant from this injector.
• the position of the second holes can also be controlled not with respect to the chamber bottom, but with respect to the injectors which are respectively closest to them.
• the position of the second holes can be controlled independently of the position of the first holes.
• the first holes and the second holes having in common the same nearest injector are located equidistant from this injector. This makes it possible to have a radially homogeneous temperature field.
• all the first and / or second holes are respectively located at the same distance from the injector that is closest to them. Thanks to these provisions, the temperature field is symmetrical of revolution around the axis of the combustion chamber. It is therefore more stable and easier to control.
• the first holes and / or the second holes are arranged in arcs of circles centered on the injectors respectively closest.
• the first wall is a radially outer wall and the second wall is a radially inner wall.
• the opposite is also possible.
• the present disclosure also relates to a turbomachine comprising an annular combustion chamber as previously described.
• FIG. 1 shows a longitudinal section of a sector of a combustion chamber
• FIG. 2 is a radial view of part of the first wall according to a first embodiment, in the direction II of FIG. 1;
• FIG. 4 is a radial view of part of the first wall according to a second embodiment, in the direction IV of FIG. 3.
• FIG. 1 shows a longitudinal section of a sector of a combustion chamber 10 of an aircraft turbine engine.
• the combustion chamber 10 is annular with a longitudinal axis X. It is delimited by a first substantially annular wall 12 around the axis X, here a radially outer wall, by a second substantially annular wall 13 about the axis X, here a radially inner wall, and a chamber bottom 14 which connects an end of the first wall 12 and the end facing the second wall 13 so as to close the upstream end of the combustion chamber 10.
• the bottom chamber 14 is here annular.
• the annular combustion chamber 10 further comprises a plurality of fuel injectors 16 which inject the fuel into the combustion chamber 10.
• the injectors 16 are distributed around the longitudinal axis X. In the present embodiment, the injectors are arranged to through the chamber bottom 14. Each injector 16 defines an injection direction I.
• first wall 12 comprises first holes formed by the first primary holes 18 and possibly the first dilution holes 20.
• second wall 13 comprises second holes formed by the second primary holes 19 and possibly the second dilution holes 21.
• At least three, preferably at least four, of the first holes 18 having in common the first injector 16 as the nearest injector are located along the a curve C strictly convex, in radial view, the concavity of the curve C being turned towards the first injector 16.
• These first holes 18 may be consecutive holes, adjacent to each other, in particular in a circumferential direction. More precisely, there are shown here six first holes 18, which are in this example first primary holes 18, arranged along the strictly convex curve C.
• the curve C is an arc of a circle, in this case centered on the first injector 16 and typically on the injection point A of said first injector 16.
• the first holes 18 having in common the same injector the closer, namely the first injector 16 are located equidistant D of this injector.
• the flame 24 is stabilized by the recirculation zone 26 and fed by the suspended fuel 22.
• the injection direction I is coplanar with the X axis of the combustion chamber.
• Figures 3 and 4 are views respectively similar to those of Figures 1 and 2, in a second embodiment.
• the elements corresponding or identical to those of the first embodiment will receive the same reference sign, to the number of hundreds, and will not be described again.
• the injectors 116 are not arranged on the chamber bottom 114.
• the injectors 116 are disposed on the first wall 112.
• the injectors 116 are in position. further downstream of the chamber bottom 114.
• the injection direction I is non-coplanar with the axis X of the combustion chamber .
• the injection direction I has a non-zero component in the circumferential direction around the axis X.
• the injection direction I has an axial component in the direction of the chamber bottom 114.
• the flow of air is represented by arrows.
• the air comes from an outlet 130 of a compressor and enters the combustion chamber 110 through the injectors 116, the first primary holes 118, the second primary holes 119, the first dilution holes 120 and the second dilution holes 121.
• the combustion gases are discharged to the inlet 132 of a turbine.
• first holes 118 for at least one first injector 116, at least three, preferably at least four of the first holes 118 having in common the first injector 116 as the nearest injector are located along a curve C strictly convex, in radial view, the concavity of the curve C being turned towards the first injector 116. More precisely, there are shown here six first holes 118, which are in this example first primary holes 118, of which four are arranged along the strictly convex curve C. The first three holes 118 shown in the lower right corner of Figure 4 being aligned, they can not be all three on the same strictly convex curve.
• the location of the air inlets (here the first holes 118) is optimized, the first holes being positioned in coherence with the physical phenomena within the combustion chamber 110.
• the flame 124 is stabilized by the recirculation zone 126 and supplied with the fuel in suspension 122.
• the position of the primary holes 118 along a strictly convex curve and whose concavity is turned towards the first injector 116, such as the curve C in FIG. 4, makes it possible to stop the recirculation zone 126 and ensures better recirculation of the flue gas and a homogenization of the temperature field in the combustion chamber 110.
• the described embodiments have been detailed in the case of a single injector 16, 116 and for the first holes 18, 118 of the first wall 12, 112, similar examples could describe the distribution of the second holes on the second one. wall.
• the second holes 19, 119 having in common the same injector 16, 116 closest can be located equidistant from this injector. This distance may be different from the distance D between the first holes 18, 118 of the injector 16, 116, or equal as shown in Figure 1.
• the distance between the first and / or second holes and their nearest injector may vary from one injector to another, or be identical for all injectors.
• first and / or second holes and their nearest injector may vary according to the type of holes, for example be different for the first primary holes 18, 118 and the first dilution holes 20, 120 who nevertheless have the same injector 16, 116 the nearest.
• the first embodiment could be applied to a combustion chamber of the type of FIG. 3 having injectors located on one of the annular walls, and the second embodiment of FIG. realization could apply to a chamber of combustion of the type of Figure 1 having injectors located on the chamber bottom.

Landscapes

• 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)
• Turbine Rotor Nozzle Sealing (AREA)

Priority Applications (1)

Applications Claiming Priority (2)

Publications (2)

Family

ID=54979773

Family Applications (1)

Country Status (10)

Family Cites Families (19)

• 2015
  • 2015-10-06 FR FR1559491A patent/FR3042023B1/fr not_active Expired - Fee Related
• 2016
  • 2016-10-04 EP EP16787502.0A patent/EP3359880B1/de active Active
  • 2016-10-04 US US15/765,823 patent/US10895383B2/en active Active
  • 2016-10-04 WO PCT/FR2016/052539 patent/WO2017060605A1/fr active Application Filing
  • 2016-10-04 CA CA3000922A patent/CA3000922A1/fr not_active Abandoned
  • 2016-10-04 RU RU2018116261A patent/RU2718375C2/ru active
  • 2016-10-04 KR KR1020187009802A patent/KR20180063120A/ko unknown
  • 2016-10-04 CN CN201680058929.7A patent/CN108139077B/zh active Active
  • 2016-10-04 JP JP2018517607A patent/JP2018534518A/ja not_active Ceased
  • 2016-10-04 PL PL16787502T patent/PL3359880T3/pl unknown

Also Published As

Similar Documents

Legal Events