EP2718627B1 - Ringförmige brennkammer für eine turbomaschine - Google Patents

Ringförmige brennkammer für eine turbomaschine Download PDF

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Publication number
EP2718627B1
EP2718627B1 EP12731106.6A EP12731106A EP2718627B1 EP 2718627 B1 EP2718627 B1 EP 2718627B1 EP 12731106 A EP12731106 A EP 12731106A EP 2718627 B1 EP2718627 B1 EP 2718627B1
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EP
European Patent Office
Prior art keywords
annular
annular wall
combustion chamber
tongues
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.)
Active
Application number
EP12731106.6A
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English (en)
French (fr)
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EP2718627A2 (de
Inventor
Bernard CARRERE
Nicolas SAVARY
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Helicopter Engines SAS
Original Assignee
Turbomeca SA
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Publication date
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Priority to PL12731106T priority Critical patent/PL2718627T3/pl
Publication of EP2718627A2 publication Critical patent/EP2718627A2/de
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Publication of EP2718627B1 publication Critical patent/EP2718627B1/de
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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
    • F23R3/60—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
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00017—Assembling combustion chamber liners or subparts
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49323—Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T403/00—Joints and connections
    • Y10T403/70—Interfitted members
    • Y10T403/7005—Lugged member, rotary engagement

Definitions

  • the invention relates to the field of turbomachine combustion chambers, and more particularly to the field of turbomachine annular combustion chambers and in particular, but not exclusively, to a helicopter turbine engine.
  • a conventional turbomachine annular combustion chamber has an axial direction, a radial direction and an azimuthal direction, and comprises a first annular wall and a second annular wall, each annular wall delimiting at least a portion of the chamber of the combustion chamber. annular.
  • the first and second annular walls can be assembled by welding, axial interlocking or bolting. Joining by welding makes it impossible to dismantle the first and second walls, for example for maintenance or for the replacement of one of these walls.
  • the assembly by axial interlocking has the disadvantage of not being sealed, combustion gases can escape through the fitting areas of the first and second annular wall.
  • the assembly by bolting has the disadvantage of promoting the appearance of cracks and fissures in the vicinity of the bolt screw engaging holes, which weakens the combustion chamber.
  • the patent US 5,737,913A shows an annular combustion chamber according to the preamble of claim 1.
  • An object of the present invention is to remedy at least substantially the aforementioned drawbacks.
  • the invention achieves its goal by means of an annular turbomachine combustion chamber having an axial direction, a radial direction and an azimuth direction, comprising a first annular wall and a second annular wall, each annular wall delimiting at least a portion of the enclosure of the annular combustion chamber, wherein the first annular wall and the second annular wall have complementary assembly means which cooperate by azimuthal interlocking.
  • first annular wall comprises first complementary assembly means and that the second wall annular has second complementary assembly means, the first and second complementary assembly means being respectively complementary to one another so as to cooperate by interlocking.
  • the first complementary means cooperate by azimuthal engagement with the second complementary means.
  • first and second complementary assembly means are nested or engaged with each other by rotating them relative to each other around the axial direction of the combustion chamber.
  • azimuthal engagement makes it possible to reduce the leakage of combustion gases with respect to an axial engagement. Since radial thermal expansion is less important than axial thermal expansion, an azimuth interlocking connection makes it possible to maintain permanent contact between the first and second annular walls, thus ensuring reduced or zero gas leaks under all conditions. of uses of the combustion chamber. In addition, such azimuthal interlocking makes it possible to use reduced or even zero clearance compared to an axial interlocking. Moreover, the interlocking of the first and second annular walls makes it possible to disassemble them.
  • the assembly by interlocking azimuth has the advantage of combining the removable appearance and the appearance of the reduction of gas leaks. combustion or even negligible or no leakage.
  • such an assembly by azimuth interlocking is easier to achieve than the assemblies of the state of the art.
  • the azimuthal direction of the interlock makes it possible to align and center around the axial direction more easily than in the state of the art.
  • the assembly according to the invention does not use a bolt, it avoids the formation of cracks and fissures.
  • the assembly being made by azimuthal engagement, the radial and axial thermal expansions are easily supported by the first and second complementary assembly means, which can slide while maintaining the interlocking relative to each other .
  • these slips on the one hand compensate thermal expansion while maintaining a geometry of the assembly satisfactory, and allows on the other hand to avoid blockages favoring, during thermal expansion, the appearance of cracks and fissures.
  • the complementary assembly means comprise a plurality of first tongues extending azimutally in a first direction from the first annular wall and a plurality of second tongues extending azimuthally in a second direction, opposite to the first direction, since the second annular wall, the first and second tabs cooperating by azimuth interlocking.
  • each first tab corresponds to a second tongue with which the first tab cooperates by interlocking.
  • tabs of the first tabs cooperate with the same number of second tabs.
  • the complementary assembly means comprise ten first tongues and twelve second tongues
  • only three first tongues can cooperate by azimuthal interlocking with three second tongues.
  • the first ten tongues cooperate with ten second tongues.
  • the first and second tongues deform elastically during azimuthal interlocking.
  • the first and second tongues are therefore elastic tongues. This allows in particular to assemble the first wall and the second wall with a predetermined tightening torque.
  • the second annular wall comprises as many second tongues as the first annular wall comprises first tongues, each first tab cooperating by azimuth interlocking with a second tongue. This makes it possible to improve the mechanical strength of the assembly and to reduce the leakage of combustion gases.
  • the first annular wall comprises a first annular flange extending radially while the second annular wall comprises a second annular flange extending radially, the first and the second flange cooperating axially in support.
  • first and the second flange cooperate in support when the complementary assembly means are nested.
  • the cooperation in support of the first flange with the second flange makes it possible to block the first wall relative to the second wall in a direction along the axial direction.
  • first and second annular flanges advantageously form joining surfaces cooperating in support with each other in order to further reduce any leakage of combustion gases.
  • first tongues are formed in the first annular flange while the second tongues are formed in the second annular flange.
  • first and second annular flanges cooperate in a bearing in a first direction in the axial direction, while the first and second tongues cooperate in bearing, when they are nested azimuthally, in a second direction, opposite to the first direction, according to the axial direction.
  • the complementarity of the flanges and tongues on the one hand to ensure a reliable assembly and mechanically resistant, and on the other hand to further reduce any leakage of combustion gas.
  • the tabs compensate by sliding relative to each other possible thermal expansion differentials, including radial expansions.
  • the assembly is insensitive to thermal expansion and the nesting remains reliable regardless of the thermal conditions of use of the combustion chamber.
  • the first and second tabs are machined by laser cutting (the first and second annular walls being metallic). This makes it possible to form the tongues during machining of the first or second annular wall in a single operation. This improves the precision of the cut, and thus the quality of the assembly (increased mechanical strength, decreased leakage).
  • the first tabs form a preformed angle in a first direction in the axial direction with the first flange while the second tabs form a preformed angle. in a second direction, opposite to the first direction, in the axial direction with the second flange.
  • the tongues thus preformed are easier to nest with each other.
  • the first and second tabs each form a preformed angle of between 1 ° and 5 ° (degree of angle) respectively with the first and second flanges. More preferably, the first and second tabs each form a preformed angle of about 2 ° (degree of angle) respectively with the first and second flanges.
  • the term "about” means an angle value plus or minus one half degree angle (i.e. here 2 ° ⁇ 0.5 °). This value of 2 ° is used to form resilient tongues in the axial direction, having a satisfactory rigidity to ensure a predetermined azimuthal engagement torque, and a small footprint.
  • the combustion chamber comprises rotational locking means of the second annular wall relative to the first annular wall (or vice versa).
  • the locking means block the relative movements in the azimuthal direction of the first and second annular wall.
  • the locking means lock this interlocking and prevent additional assembly means to dislocate. This ensures greater reliability of the assembly of the first and second annular walls.
  • the first annular wall has at least one first locking means while the second wall has at least one second locking means, at least one first locking means cooperating with at least one second locking means for locking in rotation the first annular wall with respect to the first annular wall.
  • the first wall comprises a plurality of first locking means while the second wall comprises a plurality of second locking means, the first or second blocking means being uniformly azimuthally distributed while the other blocking means among the first and the second blocking means are not uniformly azimuthally distributed.
  • the locking means comprise at least one securing screw of the first annular wall with the second annular wall.
  • the screw passes through and secures the first annular flange and the second annular flange.
  • the securing screw is either directly screwed into the wall thickness (ie cooperates directly by screwing with the first and second annular flanges), or held by means of a nut, the assembly forming a bolt clamping the first and second annular flanges. Note that such a screw does not generate cracks or cracks in the vicinity of the engagement holes through the flanges because it does not block thermal expansion and does not generate local stresses capable of creating cracks or fissures.
  • the first wall may comprise a single or a plurality of first holes for passing the screw, this or these first holes forming one or more first locking means
  • the second wall may comprise a single or a plurality of second holes for passing the screw, this or these second holes forming one or the second locking means.
  • a first locking means (or first hole) cooperates by coupling, via the screw, with a second locking means (or second hole) for locking in rotation the first annular wall relative to the first annular wall.
  • the locking means comprise at least a first projection integral with the first annular wall and at least one second projection integral with the second annular wall, the complementary assembly means cooperating azimuthally by interlocking in a first direction, and wherein the first projection and the second projection cooperate azimuthally by resilient engagement in the first direction while cooperating azimutally abutting in a second direction opposite to the first direction.
  • the first projection engages with the second projection.
  • one or both protrusions deforms elastically so as to allow the passage of a protrusion beyond the other projection.
  • the engagement of the first and second annular wall is blocked azimutally, in a first direction by the complementary assembly means which are at the end of stroke or blocked (for example a tightening torque greater than the forces generated by the vibrations or thermal expansion differentials within the combustion chamber to unlock them in this first direction) and in a second direction opposite to the first direction, by the two projections cooperating in abutment.
  • the locking means comprise a plurality of first projections and a plurality of second projections, at least one first projection cooperates with a second projection, one or more other (s) first projection (s) can also cooperate (each) with another second projection.
  • the first projection extends substantially radially from the first flange while the second projection extends substantially radially from the second flange.
  • first projection or projections form first locking means while the second or second projections form second locking means.
  • the locking means comprise at least one foldable blade formed in one flange of the first or the second annular flange engaged in one day formed in the other flange of the first or the second annular flange.
  • first or second flange has a foldable blade while the other flange of the first to the second flange has a day (ie window or cut) in which, when the complementary assembly means are nested azimuthally, one engage the folding blade by folding it.
  • the day is open on the side of the free edge of the flange and forms a U.
  • the vertical edges of the U limit and / or block the relative movements in the azimuth direction of the first and second annular walls cooperating in abutment with the edges of the folded blade.
  • the foldable blade or blades form first coupling means while the day or days form second coupling means (or vice versa).
  • the invention also relates to a turbomachine comprising a combustion chamber according to the invention.
  • the annular combustion chamber comprises rotational locking means of the second annular wall with respect to the first annular wall, and said method further comprises the step of locking in rotation (in the azimuthal direction) the second annular wall. relative to the first annular wall.
  • the figures 1 , 1A, 1B, 2 , 3 , 4A and 4B represent a first embodiment of the combustion chamber according to the invention corresponding to the first variant mentioned above.
  • the combustion chamber 10 comprises a first annular wall 12 and a second annular wall 14.
  • the combustion chamber 10 has an axial direction X (along the X axis), a radial direction R and an azimuthal direction Y.
  • the combustion chamber 10 shows a symmetry of revolution along the axis X.
  • the first wall 12 is the outer casing of the flame tube 50, the latter comprising an inner casing 16 and a chamber bottom 18.
  • the flame tube 50 receives fuel injectors 52 and defines the enclosure where the fuel ignites, ie where the combustion takes place.
  • the second wall 14 forms an outer bend and serves as a deflector for guiding the flow of gases from the flame tube 50.
  • this combustion chamber 10 is an annulus of the inverted flow type, but the invention is not limited to this particular type of combustion chamber.
  • the first and second annular walls may be other walls than the wall of the outer casing and the wall of the outer elbow.
  • the first annular wall 12 has a first annular flange 12a which extends radially outwardly of the combustion chamber 10, while the second annular wall 14 has a second annular flange 14a which also extends radially outwards. of the combustion chamber 10.
  • the first flange 12a has N first tabs 12b oriented in a first azimuthal direction while the second flange has N second tabs 14b oriented in a second azimuth direction opposite to the first azimuthal direction.
  • the orientation of a tongue is defined by the direction in which it extends from its proximal end to its distal or free end.
  • the first and second tabs 12b and 14b have a similar azimuthal length and are all uniformly angularly distributed over the first and second flanges 12a and 14a, respectively. In other words, the angular space separating two adjacent tongues is identical for all the tongues.
  • each flange and tongue The radial extent of each flange and tongue is identical.
  • the tongues extend radially on only one radial portion of each flange (ie does not extend over the entire radial width of the flanges) to ensure a good seal to the combustion gas of the assembly of the first and the second flange.
  • the first and second flanges 12a and 14a have a radially inner portion, and a radially outer portion in which the tabs are formed.
  • the inner radial portion extends radially over 4 mm (four millimeters).
  • the first and second annular flanges 12a and 14a respectively have M first through holes 12c and M second through holes 14c to engage a screw 20 (cf. fig.3 ).
  • the set of first and second holes 12c and 14c, and the screw 22 form rotational locking means.
  • there are eighteen first and second holes, that is M 18.
  • the second annular wall 14 is presented opposite the first annular wall 12 as shown in FIG. figure 1 these two walls 12 and 14 are brought axially together so that the distal ends of the first tongues 12b are axially arranged between the distal ends of the second tongues 14b and the second flange 14a (or vice versa, cf. Fig. 2 ).
  • the complementary means of assemblies are brought face to face, and the first and second tongues 12b and 14b are nested azimuthally by rotating, according to the thick line arrow on the figure 3 the second annular wall 14 around the axis X of the combustion chamber 10.
  • the axial inclination of the first and second tongues (or the angle formed by each tongue) and their rigidity leads to the first and the second flange 12a and 14a bear against each other, as shown in FIG. figure 3 .
  • a handling pin 14d protrudes from the periphery of the second flange 14a (cf. fig.1 and 1B ).
  • the holes 14c have an oblong shape oriented radially, to facilitate the insertion of the screw 22 through the two holes 12c and 14c. In particular, this oblong shape compensates for a possible lack of coaxiality between the first and second annular wall 12 and 14, or a hole machining defect.
  • first and second holes are azimutally distributed as follows.
  • the first holes 12c are uniformly distributed azimuth (cf. Fig. 4A ).
  • ⁇ 360 ° / M.
  • the azimuthal distribution of the first and second holes can be reversed.
  • the first holes form first blocking means while the second holes form second blocking means, and their number may of course be different.
  • the figures 5 , 5A, 5B, 5C and 5D represent a second embodiment of the combustion chamber of the invention corresponding to the second variant described above. Only the locking means differ from the first embodiment, the common parts between the first and the second embodiment not being described again and retain their reference sign. In particular, the azimuthal engagement of the first and second tabs 12b and 14b is performed in the same manner as for the first embodiment.
  • the blocking means of the combustion chamber 110 comprise on the one hand a number P of first projections 112 integral with the first wall 12 and secondly a same number P of second projections 114 in solidarity with second wall 14.
  • Each first and second projections 112 and 114 form a hook having a shaped profile. at L, the top of the vertical bar of the L being connected to the respective annular flange while the horizontal bar of the L extends axially.
  • the plate 112a and 114a formed by the horizontal bar of the L-shaped hook of each projection 112 and 114 is inclined respectively by an angle ⁇ and ⁇ 'with respect to the azimuthal direction (cf. Fig. 4A ), the direction of inclination of the plates 112a and 114a of the first and second projections 112 and 114 being the same.
  • the Figures 5A to 5D represent four relative positions of a first projection 112 relative to a second projection 114 during the azimuthal interlocking of the first and second tongues.
  • first and second tabs 12b and 14b are not engaged (position shown on the figure 2 ), or at the beginning of azimuth interlocking, the first and second projections 112 and 114 do not cooperate as shown in FIG. Figure 5A .
  • the first and second protrusions engage with each other by successively moving from the position 5A to the position 5B and from the position 5B at the position 5C, the second annular wall 12 being displaced in rotation along the arrow of the FIGS.
  • a radial shoulder is formed between the projections 112 and 114, blocking the azimuthal movements of disengagement of the first and second tongues 12b and 14b (opposite direction to the arrow). of the Figures 5B and 5C ).
  • the first projection 112 and the second projection 114 cooperate by elastic engagement in a first azimuthal direction on the Figures 5B and 5C (direction of the arrow) while cooperating abutting in a second azimuthal direction opposite to the first azimuthal direction in the figure 5D .
  • first projection 112 cooperates in abutment in the second direction with a second projection 114, the first and second projections are distributed azimuthally in the same manner as the first and second holes of the first embodiment.
  • first projections 112 are uniformly distributed azimuth while the second projections 114 are not uniformly distributed azimuth.
  • the azimuthal distribution of the first and second projections may be reversed. It is understood that the first projections form first locking means while the second projections form second blocking means, and their number may of course be different.
  • the figure 5 represents a clamping configuration where a first and a second projection cooperate in abutment and in elastic engagement (see I), whereas P / 2-1 pairs of first and second projections the elastic engagement is not completed (azimuthally to right of the pair I of projections, see II and III) and that the first and second projections of the P / 2 other pairs of first and second projections are engaged elastically but are spaced azimutally so that they do not do not cooperate in abutment (azimutally to the left of the pair I of projections, see IV and V).
  • the figures 6 , 6A and 6B represent a third embodiment of the combustion chamber of the invention corresponding to the second variant described above. Only the locking means differ from the first and second embodiments, the common parts between the first, the second and the third embodiment are not described again and retain their reference sign. In particular, the azimuthal engagement of the first and second tongues 12b and 14b is carried out in the same manner as for the first and second embodiments.
  • the blocking means of the combustion chamber 210 comprise on the one hand a number Q foldable blades 212 formed in the first flange 12a and secondly the same number Q of days 214 arranged of the second flange 14a.
  • the days 214 have a U shape open on the outer periphery of the flange 14a.
  • the days are formed in the first flange while the folding blades are formed in the second flange.
  • the foldable blades form first blocking means while the days form second blocking means, and their number may of course be different.
  • the Figures 6A and 6B represent two relative positions of foldable blades 212 with respect to days 214 during the azimuthal engagement of the first and second tongues.
  • the second wall 14 is pivoted about the axis X to engage the first and second tongues 12b and 14b according to the arrow of the Figure 6A , it tends to bring 214 days vis-à-vis the blades 212.
  • ⁇ 20 °
  • ⁇ ' 20.1 °
  • ⁇ " 18.3 °.
  • this angular spacing can be reversed.
  • a day 214 is vis-à-vis a foldable blade 212 so as to engage the blade 212, in the folding by folding, in day 214 (cf. Fig. 6B ).
  • the figure 6 represents a clamping configuration where a foldable blade 212 is engaged in a day 212 (see I) while Q / 2-1 blades 212 are azimutally shifted to the left of Q / 2-1 days 214 facing (azimutally right) of the pair I of projections, see II and III) and that Q / 2 blades 212 are shifted azimutally to the right (on the figure 6 ) of Q / 2 days opposite (azimutally to the left of the pair I of projections, see IV and V) so that they can not be engaged in the days opposite.
  • a blade 212 being engaged in a day 214, the blade 212 and the day 214 cooperate azimutally in both directions in abutment and block the relative rotations about the axis X of the first and the second wall 12 and 14.
  • the angular distribution of the first and second blocking means can be reversed.
  • the figure 7 represents a helicopter turbine engine 300 comprising an annular combustion chamber 10.
  • the turbine engine 300 is equipped with a combustion chamber 110 or 210.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Portable Nailing Machines And Staplers (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Supercharger (AREA)

Claims (9)

  1. Ringförmige Brennkammer (10, 110, 210) für eine Turbomaschine, die eine Axialrichtung (X), eine Radialrichtung (R) und eine Azimuthalrichtung (Y) aufweist, umfassend eine erste ringförmige Wand (12) und eine zweite ringförmige Wand (14), wobei jede Wand mindestens einem Teil des Gehäuses der ringförmigen Brennkammer (10, 110, 210) begrenzt, wobei die erste ringförmige Wand (12) und die zweite ringförmige Wand (14) komplementäre Montagemittel (12b, 14b) aufweisen, die durch azimuthales Ineinanderfügen zusammenwirken, dadurch gekennzeichnet, dass die komplementären Montagemittel eine Vielzahl von ersten Laschen (12b), die sich azimuthal in eine erste Richtung von der ersten ringförmigen Wand (12) aus erstrecken, und eine Vielzahl von zweiten Laschen (14b) umfassen, die sich azimuthal in eine zweite Richtung, die zur ersten Richtung entgegengesetzt ist, von der zweiten ringförmigen Wand (14) aus erstrecken, wobei die ersten und zweiten Laschen (12b, 14b) durch azimuthales Ineinanderstecken zusammenwirken.
  2. Ringförmige Brennkammer (10, 110, 210) nach Anspruch 1, bei der die erste ringförmige Wand (12) einen ersten ringförmigen Flansch (12a) umfasst, der sich radial erstreckt, während die zweite ringförmige Wand (14) einen zweiten ringförmigen Flansch (14a) umfasst, der sich radial erstreckt, wobei der erste und der zweite Flansch (12a, 14a) in axialer Abstützung zusammenwirken.
  3. Ringförmige Brennkammer (10, 110, 210) nach Anspruch 2, bei der die ersten Laschen (12b) in dem ersten ringförmigen Flansch (12a) ausgebildet sind, während die zweiten Laschen (14b) in dem zweiten ringförmigen Flansch (14a) ausgebildet sind.
  4. Ringförmige Brennkammer (10, 110, 210) nach einem der Ansprüche 1 bis 3, umfassend Mittel zur Drehfeststellung (12c, 14c, 22; 112, 114; 212, 214) der zweiten ringförmigen Wand (14) in Bezug zur ersten ringförmigen Wand (12).
  5. Ringförmige Brennkammer (110) nach Anspruch 4, bei der die Feststellungsmittel mindestens einen ersten Vorsprung (112), der mit der ersten ringförmigen Wand (12) verbunden ist, und mindestens einen zweiten Vorsprung (114), der mit der zweiten ringförmigen Wand (14) verbunden ist, umfassen, wobei die komplementären Montagemittel azimuthal durch Ineinanderstecken in eine erste Richtung zusammenwirken, und bei der der erste Vorsprung (112) und der zweite Vorsprung (114) azimuthal durch elastisches Eingreifen die erste Richtung zusammenwirken, während sie azimuthal am Anschlag in eine zweite, zur ersten Richtung entgegengesetzte Richtung zusammenwirken.
  6. Ringförmige Brennkammer (210) nach den Ansprüchen 2 und 4, bei der die Feststellungsmittel mindestens eine faltbare Lamelle (212) umfassen, die in einen Flansch unter dem ersten oder dem zweiten ringförmigen Flansch (12a, 14a) ausgebildet ist und in eine Öffnung (214) eingreift, die in dem anderen Flansch unter dem ersten oder dem zweiten ringförmigen Flansch (12a, 14a) ausgenommen ist.
  7. Turbomaschine (300), umfassend eine ringförmige Brennkammer (10, 110, 210) nach einem der Ansprüche 1 bis 6.
  8. Montageverfahren, um eine ringförmige Brennkammer (10, 110, 210) nach einem der Ansprüche 1 bis 6 zusammenzubauen, umfassend die Schritte:
    - Anordnen der komplementären Montagemittel (12b, 14b) der ersten und zweiten ringförmigen Wände (12, 14) einander gegenüberliegend,
    - azimuthales Ineinanderfügen der komplementären Montagemittel (12b, 14b) durch Drehen der zweiten ringförmigen Wand (14) in Bezug zur ersten ringförmigen Wand (12).
  9. Montageverfahren nach Anspruch 8, um eine ringförmige Brennkammer (10, 110, 210), umfassend Drehfeststellungsmittel (12c, 14c, 22; 112, 114; 212, 214) der zweiten ringförmigen Wand (14) in Bezug zur ersten ringförmigen Wand (12), zusammenzubauen, wobei das Verfahren ferner den Schritt der Drehfeststellung der zweiten ringförmigen Wand (14) in Bezug zur ersten ringförmigen Wand (12) umfasst.
EP12731106.6A 2011-06-08 2012-06-04 Ringförmige brennkammer für eine turbomaschine Active EP2718627B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL12731106T PL2718627T3 (pl) 2011-06-08 2012-06-04 Pierścieniowa komora spalania maszyny wirowej

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1154984A FR2976346B1 (fr) 2011-06-08 2011-06-08 Chambre de combustion annulaire de turbomachine
PCT/FR2012/051240 WO2012168636A2 (fr) 2011-06-08 2012-06-04 Chambre de combustion annulaire de turbomachine

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EP2718627A2 EP2718627A2 (de) 2014-04-16
EP2718627B1 true EP2718627B1 (de) 2015-08-26

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US (1) US8925331B2 (de)
EP (1) EP2718627B1 (de)
JP (1) JP6073299B2 (de)
KR (1) KR102001690B1 (de)
CN (1) CN103597285B (de)
CA (1) CA2838168C (de)
ES (1) ES2548697T3 (de)
FR (1) FR2976346B1 (de)
PL (1) PL2718627T3 (de)
RU (1) RU2600829C2 (de)
WO (1) WO2012168636A2 (de)

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FR3017693B1 (fr) * 2014-02-19 2019-07-26 Safran Helicopter Engines Chambre de combustion de turbomachine
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WO2016032515A1 (en) * 2014-08-29 2016-03-03 Siemens Energy, Inc. Bayonet arrangement of a casing component using inclined hooks and method for attaching and removing this component
UA119005C2 (uk) * 2015-04-02 2019-04-10 Бті Гумковскі Сп. З О.О. Сп. К. Пальник твердопаливного котла
RU186048U1 (ru) * 2018-10-08 2018-12-27 Публичное Акционерное Общество "Одк-Сатурн" Узел упругого соединения жаровой трубы и газосборника камеры сгорания газотурбинного двигателя
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FR3095499B1 (fr) 2019-04-23 2021-06-11 Safran Helicopter Engines Injecteur d’un melange d’air et de carburant pour une chambre de combustion d’une turbomachine
FR3119881B1 (fr) * 2021-02-18 2023-12-22 Safran Ceram Sous ensemble comportant des moyens de compensation d'une difference de dilatation

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Also Published As

Publication number Publication date
CN103597285A (zh) 2014-02-19
FR2976346A1 (fr) 2012-12-14
WO2012168636A3 (fr) 2013-03-28
WO2012168636A2 (fr) 2012-12-13
US20140109595A1 (en) 2014-04-24
JP6073299B2 (ja) 2017-02-01
RU2013158179A (ru) 2015-07-20
CN103597285B (zh) 2015-09-30
JP2014516152A (ja) 2014-07-07
FR2976346B1 (fr) 2013-07-05
KR20140037885A (ko) 2014-03-27
EP2718627A2 (de) 2014-04-16
PL2718627T3 (pl) 2015-12-31
ES2548697T3 (es) 2015-10-20
US8925331B2 (en) 2015-01-06
RU2600829C2 (ru) 2016-10-27
CA2838168C (fr) 2018-10-23
KR102001690B1 (ko) 2019-07-18
CA2838168A1 (fr) 2012-12-13

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