EP1939528B1 - Deflektor für rückwärtigen Teil der Brennkammer, damit ausgestattete Brennkammer und Turbostrahltriebwerk, das beide umfasst - Google Patents

Deflektor für rückwärtigen Teil der Brennkammer, damit ausgestattete Brennkammer und Turbostrahltriebwerk, das beide umfasst Download PDF

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Publication number
EP1939528B1
EP1939528B1 EP07122639.3A EP07122639A EP1939528B1 EP 1939528 B1 EP1939528 B1 EP 1939528B1 EP 07122639 A EP07122639 A EP 07122639A EP 1939528 B1 EP1939528 B1 EP 1939528B1
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EP
European Patent Office
Prior art keywords
deflector
combustion chamber
sides
chamber
central region
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
EP07122639.3A
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English (en)
French (fr)
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EP1939528A1 (de
Inventor
Patrice Commaret
Didier Hernandez
David Locatelli
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 Aircraft Engines SAS
Original Assignee
SNECMA Services SA
SNECMA SAS
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Publication date
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Publication of EP1939528A1 publication Critical patent/EP1939528A1/de
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Publication of EP1939528B1 publication Critical patent/EP1939528B1/de
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    • 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

Definitions

  • the present invention relates to the technical field of combustion chambers for turbojet engines.
  • it relates to a thermal protection screen, or baffle, for a combustion chamber bottom. It also aims a combustion chamber with at least one such deflector.
  • a turbojet engine equipped with such a combustion chamber and / or at least one such deflector.
  • a conventional combustion chamber, called divergent, is illustrated on the figure 11 , which is an axial section showing a half of the combustion chamber, the other half of which is deduced by symmetry with respect to the axis (not shown) of the turbojet engine.
  • the combustion chamber 110 is comprised in a diffusion chamber 130 which is an annular space defined between an outer casing 132 and an inner casing 134, into which a compressed oxidant originating upstream of a compressor (not shown) by the compressor is introduced. intermediate of an annular diffusion duct 136.
  • said divergent 110 has an outer wall 112 and an inner wall 114, which are coaxial and substantially conical, and which flare from upstream to downstream with a cone angle ⁇ .
  • the outer 112 and inner 114 walls of the combustion chamber 110 are interconnected upstream of the combustion chamber by a chamber bottom 116.
  • the chamber bottom 116 is a substantially frustoconical piece, which extends between two substantially transverse planes flaring from downstream to upstream.
  • the chamber bottom 116 is connected to each of the two outer 112 and inner 114 walls of the combustion chamber 110. Due to the small inclination of the combustion chamber 110, the chamber bottom 116 has a small taper. It has injection systems 118 through which pass injectors 120 which introduce fuel to the upstream end of the combustion chamber 110 where the combustion reactions take place.
  • thermal protection screens also called deflectors 122.
  • deflectors 122 are substantially flat plates arranged and brazed on an inner face of the chamber bottom 116. They are cooled by means of cooling air jets entering the chamber of combustion 110 through cooling orifices 124 drilled in the chamber bottom 116. These air jets, flowing from upstream to downstream, are guided by chamber fairings 126, through the chamber bottom 116 through the cooling orifices 124, and impact an upstream face of the deflectors 122.
  • so-called convergent combustion chambers the outer and inner walls of the combustion chamber are inclined flaring from downstream to upstream, and not from upstream to downstream as with the conventional combustion chambers, said divergent, previously described.
  • These so-called convergent combustion chambers may have a cone angle ⁇ greater than the cone angle ⁇ of the so-called diverging combustion chambers.
  • Such a large inclination of the combustion chamber affects the taper of the chamber bottom and the position of the baffles relative to the chamber bottom.
  • a combustion chamber is partially illustrated at the figure 12 , in axial section. In this figure appear an axial direction 100 parallel to the axis of the turbojet, the main direction 200 of the combustion chamber 110, and the angle ⁇ between these two axes 100, 200. Due to the significant inclination of the chamber 110, the chamber bottom 116 has a larger conicity than a traditional combustion chamber bottom. When not only the inclination of the chamber bottom 116 is important, but also the injectors 120 are present in reduced number and / or the combustion chamber 110 has a small diameter, it affects the distance D between the chamber bottom and the flat deflectors.
  • the object of the invention is to remedy these drawbacks, and proposes a thermal protection screen for chamber bottom, or deflector, which is configured in such a way that the distance D between the chamber bottom and this deflector remains constant.
  • the invention relates to a deflector for a chamber bottom of a combustion chamber of a turbojet, in the form of a plate with a hole.
  • said plate is a portion of a conical surface of revolution about a cone axis, said plate having a substantially concave face and a substantially convex face, and said plate having a contour that has four sides, among which two first sides are concentric circle arcs and centered on said cone axis, and two second sides are generator segments of said cone which connect said first sides.
  • Said deflector further comprises a central zone which surrounds said hole and a peripheral zone which surrounds said central zone, said central zone having a plane face on the side of said concave face.
  • said central zone is substantially circular.
  • said deflector has a connection zone between said peripheral zone and said central zone.
  • said central zone is a plane portion delimited by two edges which are segments of generatrices of said cone parallel to said second sides.
  • said first sides of the plate forming the baffle are each provided with a flange extending on the side of the concave face of the baffle.
  • said deflector is furthermore provided with angular positioning means.
  • said angular positioning means comprise a locking groove for receiving a locking key.
  • they also comprise a locking key intended to cooperate with a locking groove formed on said deflector.
  • the invention relates to a combustion chamber which has at least one deflector according to the first aspect.
  • said deflector is soldered to the chamber bottom.
  • Said combustion chamber further comprises angular positioning means.
  • Said angular positioning means comprise a first locking groove for receiving a locking key. They comprise, in addition, a second locking groove for cooperating with a stop finger.
  • said combustion chamber is a so-called convergent combustion chamber, having a coaxial and substantially frustoconical outer wall and inner wall which are inclined flaring from downstream to upstream.
  • the invention relates to a turbojet, which comprises a combustion chamber according to the first aspect and / or at least one deflector according to the second aspect.
  • FIG. 1 there is shown a portion of a turbojet engine 2 extending in an axial direction 100 and equipped with a combustion chamber 10.
  • This combustion chamber 10 said convergent, comprises an outer wall 12 and an inner wall 14, which are coaxial and substantially frustoconical.
  • the combustion chamber 10 is comprised in a diffusion chamber 30 which is an annular space defined between an outer casing 32 and an inner casing 34, into which a compressed oxidant originating upstream of a compressor (not shown) by the compressor is introduced. intermediate of an annular diffusion duct 36.
  • the outer 12 and inner 14 walls of the combustion chamber 10 are connected to each other upstream of the combustion chamber by a chamber bottom 16, which is a substantially frustoconical piece extending between two substantially transverse planes in s'. flaring from upstream to downstream.
  • the chamber bottom 16 is connected to each of the two outer walls 12 and inner 14 of the combustion chamber 10. It is provided with injection systems 18 through which pass injectors 20 which pass through the outer casing 32 and which introduce fuel at the upstream end of the combustion chamber 10 where the combustion reactions take place.
  • a deflector 22 is shown diagrammatically and in perspective at the figure 2 .
  • This deflector 22 is in the form of a plate which is a portion of a conical surface of a cone, this cone having a cone axis 300 and a cone angle ⁇ .
  • said cone axis 300 is substantially coincident with the axis 100 of the turbojet engine.
  • the deflector 22 has a concave face 62 and a convex face 64, and a contour having four sides 72, 74, 76, 78. Two 72, 76 of these four sides are concentric parallel circular arcs of the same axis 300.
  • the other two 74, 78 of these four sides are segments of generators of the cone, which connect the two sides 72, 76 in arcs.
  • the deflector 22 according to the embodiment comprises an injection hole 40, substantially central, intended to be opposite an injection system 18 of the chamber bottom 16 when the deflector 22 is installed on the chamber floor 16 Said injection hole 40 is a hole with a fallen edge, that is to say it has an edge 402 rising on the side of the upstream face of the deflector 22.
  • FIG 3 illustrates a portion of the chamber bottom 16 in the vicinity of an injection system 18 in which is disposed an injection bowl 206.
  • the chamber bottom 16 has a large conicity (see figure 1 ).
  • the deflector 22 is arranged parallel to the chamber bottom 16, on the inside of the combustion chamber 10. Due to the conical curvature of the deflector 22, which is similar to the conical curvature of the chamber bottom 16, said deflector 22 is parallel to said chamber bottom 16.
  • An advantage of such a deflector 22 lies in the fact that the distance D between said deflector 22 and the chamber bottom 16 is substantially constant for the entire surface of said deflector 22. As a result, such a deflector 22 can be cooled satisfactorily by air streams which impact after passing through cooling orifices 24 formed in the chamber bottom 16.
  • the figure 3 also shows the relative position of the deflector 22 with respect to the injection bowl 206.
  • the injection bowl 206 is oriented around an axis 200. It comprises a flange 208 which itself comprises a fastening flange 210 which is retained axially between a first ring 50 and the injection hole 40 of the deflector 22 and the edge 402 of the injection hole 40 of the deflector 22.
  • the chamber bottom 16 is locked between an outer shoulder 226 of the edge 402 of the injection hole 40 of the deflector 22 and a second ring 52 which is itself fixed by brazing in an outer peripheral groove 404 of the edge 402 of the injection hole 40 of the deflector 22.
  • the second ring 52 also has an inner shoulder in which fits the first ring 50, the two rings 50, 52 being fixed together by a weld bead 54.
  • This assembly is such that the flange 208 is allowed to move slightly in a plane perpendicular to the axis 200.
  • the injection bowl 206 is allowed to a slight clearance transverse to the axis 200, which allows the entry of air threads through the injection hole 40 even when the injection bowl 206 is in place.
  • These air streams represented by the arrows 60 in the figures, have the function of cooling the edge 402 of the injection hole 40 of the deflector 22, this edge 402 constituting a relatively thick zone of the deflector 22 which can not be reached by the cooling air passing through the cooling orifices 24 of the chamber bottom 16.
  • the injection bowl 206 also has a flange 220 located inside the combustion chamber 10 which is separated from the flange 208 by a groove 222, and which extends parallel to the fastening flange 210 substantially until aplomb of the inner face of the edge 402 of the injection hole 40 of the deflector 22.
  • the figure 4 shows an enlarged detail of the figure 3 . More specifically, it shows the edge 402 of the injection hole 40 of the deflector 22 and the flange 208, the flange 220 and the groove 222 of the injection bowl 206. It appears that, due to the shape conical, and not planar, deflector 22, the inner face of the deflector 22 is offset from the inner face of the flange 208. This shift, or walk, is designated by the letter M to the figure 4 . The existence of this step M is likely to create a disturbance of the flow of the cooling jets represented by the arrow 60, for example in the form of vortices, which is likely to affect the cooling of the falling edge 402 of the hole d injection 40 of the deflector 22.
  • FIGS 7-8 and 9-10 represent respectively a first variant and a second variant of an embodiment of the deflector 22, which constitutes an improvement of the first embodiment described above.
  • the characteristics of the embodiment of the deflector 22 already described are also characteristics of the two variants of the embodiment illustrated in these embodiments.
  • Figures 7 to 10 are also characteristics of the two variants of the embodiment illustrated in these embodiments.
  • the deflector 22 has a central zone 90 which surrounds the injection hole 40, and a peripheral zone 92 which surrounds the central zone 90 to the edges 72, 74, 76, 78 of the deflector 22.
  • the peripheral zone 92 has a concave conical surface.
  • said central zone 90 is circular and has a flat surface, while the peripheral zone 92 has a concave conical surface.
  • a connection zone 94 connects said central zone 90 and said peripheral zone 92.
  • said central zone 90 is between two edges 96, 98 substantially parallel to the straight sides 74, 78 of the contour of said deflector 22, and extends to the arcuate sides 72, 76 of the contour of said deflector 22. It has a flat surface.
  • the two edges 96, 98 materialize the intersection between the flat surface of said central zone 90 and the concave conical surface of the peripheral zone 92.
  • the central zone 90 has a planar surface on the concavity side of the deflector 22.
  • the distance D between said deflector 22 and the chamber bottom 16 is substantially constant for the entire surface of said deflector 22.
  • the deflector 22 can be cooled satisfactorily by air streams which come to impact after passing through cooling orifices 24 arranged in the chamber bottom 16.
  • the cooling air streams 60 may flow from outside the bowl 206 through the injection opening 40 without being disturbed by turbulence. It follows that the cooling of the dropped edge 402 of the injection hole 40 of the deflector 22 can be satisfactorily performed.
  • the flat surface of the central zone 90 and the inner face of the flange 208 of the bowl 206 are substantially in the same plane.
  • the two arcuate sides 72, 76 of the plate forming the deflector 22 are each provided with a flange 80 extending on the side of the concave face 62 of the baffle. This characteristic is common to the embodiments.
  • the flanges 80 of the deflector 22 have the function of creating a cooling film by guiding the cooling air of the deflectors 22 which is coming from the cooling orifices 24, in order to cool the outer 12 and inner 14 walls of the combustion chamber 10 .
  • the deflector 22 is provided with angular positioning means consisting of first angular positioning means and second angular positioning means. This characteristic is common embodiments.
  • the figure 6 illustrates the first angular positioning means 82, 84 which comprise a first locking groove 82 having three sections formed respectively in the chamber bottom 16, the deflector 22 and the second ring 52 and a key 84.
  • the insertion of the key 84 in said first locking groove 82 prevents relative rotation of the second ring 52 and the deflector 22 with respect to the chamber bottom 16.
  • the figure 5 illustrates the second angular positioning means 86, 88 which comprise a second locking groove 86 formed in the second ring 52 and a stop pin 88 integral with the injection bowl 206, the insertion of the finger stop 88 in said second locking groove 86 prevents relative rotation of the injection bowl 206 relative to the second ring 52.
  • the invention also relates to a combustion chamber 10 which comprises a chamber bottom 16 and at least one deflector 22 as previously described.
  • said deflector 22 is brazed to said chamber bottom 16.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Cylinder Crankcases Of Internal Combustion Engines (AREA)

Claims (12)

  1. Deflektor (22) für einen Kammerboden (16) einer Brennkammer (10) eines Turbostrahltriebwerks (2), der die Form einer Platte aufweist, die mit einem Loch (40) versehen ist, wobei die Platte ein Abschnitt einer konischen Rotationsfläche um eine Konusachse (300) ist, wobei die Platte eine im Wesentlichen konkave Seite (62) und eine im Wesentlichen konvexe Seite (64) aufweist, und die Platte einen Umriss aufweist, der vier Seiten (72, 74, 76, 78) aufweist, von denen zwei erste Seiten (72, 76) konzentrische Kreisbögen sind und auf der Konusachse (300) zentriert sind, und zwei zweite Seiten (74, 78) Kantensegmente des Konus sind, die diese ersten Seiten (72, 76) verbinden, dadurch gekennzeichnet, dass der Deflektor (22) einen mittleren Bereich (90), der das Loch (40) umgibt, und einen Randbereich (92) aufweist, der den mittleren Bereich (90) umgibt, wobei der mittlere Bereich (90) eine flache Seite auf der Seite der im Wesentlichen konkaven Seite (62) aufweist.
  2. Deflektor (22) nach Anspruch 1, dadurch gekennzeichnet, dass der mittlere Bereich (90) im Wesentlichen kreisförmig ist.
  3. Deflektor (22) nach Anspruch 2, dadurch gekennzeichnet, dass er einen Anschlussbereich (94) zwischen dem Randbereich (92) und dem mittleren Bereich (90) aufweist.
  4. Deflektor (22) nach Anspruch 1, dadurch gekennzeichnet, dass der mittlere Bereich (90) ein ebener Abschnitt ist, der von zwei Schnittlinien (96, 98) begrenzt ist, die Kantensegmente des Konus sind, die im Wesentlichen parallel zu den zweiten Seiten (74, 78) sind.
  5. Deflektor (22) nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass die ersten Seiten (72, 76) der Platte, die den Deflektor (22) bildet, jeweils mit einem Rand (80) versehen sind, der sich auf der konkaven Seite (62) des Deflektors (22) erstreckt.
  6. Brennkammer (10), dadurch gekennzeichnet, dass sie mindestens einen Deflektor (22) nach einem der Ansprüche 1 bis 5 aufweist.
  7. Brennkammer (10) nach Anspruch 6, dadurch gekennzeichnet, dass der Deflektor (22) durch Schweißen auf dem Kammerboden (16) befestigt ist.
  8. Brennkammer (10) nach einem der Ansprüche 6 oder 7, dadurch gekennzeichnet, dass sie ferner Mittel zur Winkelpositionierung (82, 84, 86, 88) aufweist.
  9. Brennkammer (10) nach Anspruch 8, dadurch gekennzeichnet, dass die Mittel zur Winkelpositionierung (82, 84, 86, 88) eine erste Blockierungsnut (84) aufweisen, die dazu bestimmt ist, einen Sperrkeil (84) aufzunehmen.
  10. Brennkammer (10) nach Anspruch 8 oder 9, dadurch gekennzeichnet, dass die Mittel zur Winkelpositionierung (82, 84, 86, 88) eine zweite Blockierungsnut (86) aufweisen, die dazu bestimmt ist, mit einem Sperrfinger (88) zusammenzuwirken.
  11. Brennkammer (10) nach einem der Ansprüche 6 bis 10, dadurch gekennzeichnet, dass sie eine konvergierende Brennkammer ist, die eine Außenwand (12) und eine Innenwand (14) aufweist, die koaxial und im Wesentlichen kegelstumpfförmig sind, die geneigt sind, indem sie sich von hinten nach vorne erweitern.
  12. Turbostrahltriebwerk (2), dadurch gekennzeichnet, dass es eine Brennkammer (10) nach einem der Ansprüche 6 bis 11 aufweist.
EP07122639.3A 2006-12-19 2007-12-07 Deflektor für rückwärtigen Teil der Brennkammer, damit ausgestattete Brennkammer und Turbostrahltriebwerk, das beide umfasst Active EP1939528B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0655657A FR2910115B1 (fr) 2006-12-19 2006-12-19 Deflecteur pour fond de chambre de combustion, chambre de combustion en etant equipee et turboreacteur les comportant

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Publication Number Publication Date
EP1939528A1 EP1939528A1 (de) 2008-07-02
EP1939528B1 true EP1939528B1 (de) 2016-06-22

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US (1) US8037691B2 (de)
EP (1) EP1939528B1 (de)
JP (1) JP5175081B2 (de)
CA (1) CA2615029C (de)
FR (1) FR2910115B1 (de)
RU (1) RU2433347C2 (de)

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US9284963B2 (en) 2013-01-28 2016-03-15 American Dryer, Inc. Blower assembly for hand dryer, with helmholtz motor mount

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Also Published As

Publication number Publication date
US20080141674A1 (en) 2008-06-19
RU2433347C2 (ru) 2011-11-10
FR2910115B1 (fr) 2012-11-16
CA2615029A1 (fr) 2008-06-19
RU2007147326A (ru) 2009-06-27
US8037691B2 (en) 2011-10-18
JP2008151498A (ja) 2008-07-03
EP1939528A1 (de) 2008-07-02
FR2910115A1 (fr) 2008-06-20
JP5175081B2 (ja) 2013-04-03
CA2615029C (fr) 2014-12-02

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