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EP3179169B1 - Procédé de montage d'une chambre de combustion d'une turbine à gaz - Google Patents

Procédé de montage d'une chambre de combustion d'une turbine à gaz Download PDF

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Publication number
EP3179169B1
EP3179169B1 EP16202400.4A EP16202400A EP3179169B1 EP 3179169 B1 EP3179169 B1 EP 3179169B1 EP 16202400 A EP16202400 A EP 16202400A EP 3179169 B1 EP3179169 B1 EP 3179169B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
chamber wall
head
accordance
recesses
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.)
Not-in-force
Application number
EP16202400.4A
Other languages
German (de)
English (en)
Other versions
EP3179169A1 (fr
Inventor
Dr.-Ing. Carsten Clemen
Dr. Kay HEINZE
Volker Herzog
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP3179169A1 publication Critical patent/EP3179169A1/fr
Application granted granted Critical
Publication of EP3179169B1 publication Critical patent/EP3179169B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/31—Retaining bolts or nuts
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • 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
    • 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

Definitions

  • the invention relates to a method for assembling a combustion chamber of a gas turbine engine according to the features of the preamble of claim 1.
  • the invention relates to a method in which a combustion chamber, in particular an annular combustion chamber of a gas turbine engine is mounted.
  • a combustion chamber in particular an annular combustion chamber of a gas turbine engine
  • an outer and an inner annular combustion chamber wall are manufactured in the usual way, for example, from sheet materials.
  • the outer and the inner combustion chamber wall can be formed single-walled. However, it is also possible to form these double-walled and to provide on the respective inside with shingles or similar components.
  • a combustion chamber of a gas turbine engine has a likewise annular top plate, which is provided with recesses through which burners are performed.
  • the top plate is connected to the outer and inner combustion chamber walls so as to mount the basic elements of the combustion chamber. Subsequently, a combustion chamber head is attached to the top plate, the outer combustion chamber wall or the inner combustion chamber wall.
  • the outer combustion chamber wall 29 has an outer flange 41, while the inner combustion wall 30 is provided with an inner flange 42.
  • the flanges are arranged at an angle to the longitudinal extent of the outer and the inner combustion chamber wall 29, 30, to be aligned parallel to the engine axis 1. According to the invention, the angle between the outer flange 41 and the outer combustion wall 29 or the inner flange 42 and the inner combustion chamber 30 is not required.
  • Fig. 3 shows a plan view of a portion of a fully assembled combustion chamber according to the prior art.
  • Fig. 2 is a sectional view according to section A shown. It can be seen that the top plate 31 is provided with an outer flange 43 and an inner flange 44. These two flanges 43 and 44 extend in the assembled state parallel to the flanges 41 and 42 of the outer and the inner combustion chamber wall.
  • the shows Fig. 2 a combustor head 32, preferably formed of a sheet metal material, which is provided with an outer flange 45 and an inner flange 46.
  • These flanges are aligned in the mounted state parallel to the flanges 41 to 44 and are bolted by means of bolts 34 and nuts 35 together with the flanges of the outer combustion chamber wall 29 and the inner combustion chamber wall 30 and the top plate 31.
  • the screwing takes place so that the central axes of the bolts extend in a radial plane, which is aligned radially to the engine axis 1.
  • the flanges 41 to 46 each form cylindrical surfaces to allow easy installation and to avoid leakage through small tolerances.
  • 31 heat shields 38 are mounted on the side facing the interior of the combustion chamber side of the top plate.
  • the number of heat shields is usually identical to the number of fuel nozzles (not shown).
  • the heat shields are screwed prior to assembly of the top plate 31 with this.
  • the Fig. 2 thus shows according to section A of Fig. 3 a fully assembled state with a plurality of circumferentially arranged bolts 34 and nuts 35.
  • the screwing of the nuts 35 is effected by not shown mounting openings of the combustion chamber head 32nd
  • the Fig. 3 shows a plan view in which a portion of the outer combustion chamber wall 29 is shown. In the mounted state, a view of the outer flange 45 of the combustion chamber head 32 results in the plan view.
  • the 4 and 5 each show sections B according to Fig. 3 , It is in Fig. 4 the combustion chamber head 32 is not yet mounted.
  • the Fig. 4 shows that the assembly is carried out by first at the periphery in the areas in which the outer flange 45 and the inner flange 46 of the combustion chamber head are provided with the recess 47, threaded bolts 48 and nuts 49 are used to the flanges 41 and 42 of the outer 29 and the inner 30 combustion chamber wall to connect with each other. This connection is made to align the combustion chamber walls 29 and 30 and the top plate 31 to each other and to be able to position.
  • some of the recesses 47 are provided on the combustion head 32. According to the number of recesses 47, the number of threaded bolts 48 or nuts 49 to be used results.
  • the combustion chamber head 32 is slid, wherein the recesses 47 are positioned so that they coincide with the threaded bolt 48 and the nuts 49. In this case, it is necessary that the combustion chamber head 32 must be manufactured very precisely and positioned during assembly in order to prevent collisions with the threaded bolts 48.
  • the object is achieved by the combination of features of claim 1, the dependent claims show further advantageous embodiments of the invention.
  • the head plate by means of distributed around the circumference arranged rivets with the outer combustion chamber wall and the inner combustion chamber wall is connected.
  • the rivets thus serve to ensure a preliminary assembly in a simple and fast way. It is not necessary, as required in the prior art, additional fittings that need to be mounted and secured. Rather, the rivets themselves are sufficient to ensure a pre-assembly of the outer and inner combustion chamber wall and the combustion chamber head.
  • a combustor of a gas turbine engine namely, an outer and an inner combustion chamber wall, a top plate, and a combustion head.
  • a pre-assembly of the top plate and the inner and outer combustion chamber walls by means of rivets As a result, before the screwing of the combustion chamber head to the preassembled module before a stable arrangement.
  • a rivet connection is simpler and more durable than a screw connection, which can also contain errors with regard to the torque to be applied and, incidentally, also increases a total weight of the combustion chamber.
  • the provision of a riveted joint results in a permanent bond without affecting the metallurgical environment, as would be the case in a welding process.
  • the rivet connection allows the avoidance of thermal distortion of the components, as may occur in a welded joint.
  • a simple and inexpensive mountable combustion chamber can be made available in a targeted manner by the combination of the provision of rivet connections for a preassembled subassembly and the final screwing operation of the combustion chamber head Weight optimization allows, as the riveted joints have a significantly lower weight than screw connections. Manufacturing technology also results in advantages through the rivet connections.
  • the outer combustion chamber wall, the inner combustion chamber wall and the top plate are provided with a multiplicity of rivet recesses which are distributed around the circumference and are aligned with one another in the assembled state prior to assembly.
  • These rivet recesses may be formed slightly different than the recesses for the implementation of the threaded bolt.
  • the rivet recesses can be formed according to the invention as a circular holes or as slots. This makes it possible in a simple manner, make an assignment, pre-assembly and / or adjustment of the outer combustion chamber wall, the inner combustion chamber wall and the top plate.
  • the rivet recesses may, for example, be provided with a countersink to introduce countersunk rivets whose heads do not protrude on the outer peripheral surface of the flanges of the combustion chamber walls and / or the top plate.
  • a riveting for the purpose of pre-assembly takes place only on some of the circumference provided Nietausappelgeber.
  • NietausNOOSE it is possible to provide only three rivets, which are distributed uniformly around the circumference, for example at a distance of 120 °.
  • the other rivet recesses remain unused.
  • the rivets used for pre-assembly can be drilled in order to allow the disassembly of the outer and the inner combustion chamber wall and the top plate.
  • some of the remaining Nietauslangauerungen can be used.
  • riveting is thus carried out at least three points on the circumference for pre-assembly.
  • the number of rivets also depends on the stability of the outer and inner combustion chamber wall and the top plate and the dimensioning of the combustion chamber.
  • the inventively provided Nietaus fundamentallessness are thus introduced according to the inventive method in addition to the recesses, by means of which in the assembled state, the combustion chamber head is screwed. It can be particularly advantageous if these fferausappelgeber and the Nietausappelgeber be mounted alternately.
  • the combustion chamber head according to the invention is preferably provided with a plurality of fferausappelisme which are arranged on the outer and the inner flange of the combustion chamber head. These fferausappelisme are arranged and dimensioned so that they are aligned with fferausappel traditions the combustion chamber walls and the top plate, so that the usual screwing can be done with deferred combustion chamber head.
  • the gas turbine engine 10 is a generalized example of a turbomachine, in which the invention can be applied.
  • the engine 10 is formed in a conventional manner and comprises in the flow direction in succession an air inlet 11, a circulating in a housing fan 12, a medium pressure compressor 13, a high pressure compressor 14, a combustion chamber 15, a high pressure turbine 16, a medium pressure turbine 17 and a low pressure turbine 18 and a Exhaust nozzle 19, which are all arranged around a central engine axis 1.
  • the intermediate pressure compressor 13 and the high pressure compressor 14 each include a plurality of stages, each of which includes a circumferentially extending array of fixed stationary vanes 20, commonly referred to as stator vanes, that radially inwardly from the core engine housing 21 into an annular flow passage through the compressors 13, 14 protrude.
  • the compressors further include an array of compressor blades 22 projecting radially outwardly from a rotatable drum or disc 26 coupled to hubs 27 of high pressure turbine 16 and mid pressure turbine 17, respectively.
  • the turbine sections 16, 17, 18 have similar stages, comprising an array of fixed vanes 23 projecting radially inward from the housing 21 into the annular flow passage through the turbines 16, 17, 18, and a downstream array of turbine rotor blades 24 projecting outwardly from a rotatable hub 27.
  • the compressor drum or compressor disk 26 and the blades 22 disposed thereon and the turbine rotor hub 27 and the turbine rotor blades 24 disposed thereon rotate about the engine axis 1 during operation.
  • the Fig. 6 shows in the sectional view A according to Fig. 7 a fully assembled state in which the outer flange 45 and the inner flange 46 of the combustion chamber head 32 and the flanges 41 and 42 of the outer combustion chamber wall 29 and the inner combustion chamber wall 30 and the outer flange 43 and the inner flange 44 of the top plate 31 by means of Screw bolt 34 and the nuts 35 are screwed.
  • the shows Fig. 6 in that the top plate 31 is screwed to at least one heat shield 38 by means of threaded bolts 39 and nuts 40.
  • Fig. 8 is in the sectional view B of the assembled state according to Fig. 6 shown.
  • the sectional view of Fig. 8 is offset by the circumference. While the section A is laid through the center axes of the threaded bolts 34, the section according to Fig. 8 (Section B) through central axes of NietausEnglishept 36 which, as in Fig. 7 is shown, are formed on the circumference alternately with gentausEnglishept 37.
  • the NietausEnglishept 36 through the Flange 41 of the outer combustion chamber wall 29 and the outer flange 43 of the top plate 31 and the inner flange 44 of the top plate 31 and the inner flange 42 of the inner combustion chamber 30 extend.
  • FIG. 8 shows that the outer flange 45 and the inner flange 46 of the combustion head 32 are slid over the flanges 41 and 42, respectively, to be bolted at locations circumferentially offset, as in Figs Fig. 6 shows.
  • the Fig. 9 shows a section C according to Fig. 7 , It can be seen that for pre-assembly of the outer flange 41 of the outer combustion chamber wall 29 and the outer flange 43 of the top plate 31 are connected by means of a rivet 33 for pre-assembly. Similarly, the inner flange 44 of the top plate 31 and the flange 42 of the inner combustion chamber wall 30 have been connected by means of a rivet 33 for pre-assembly.
  • the combustion chamber head 32 with its annular flanges 45 and 46 are pushed over the rivets 33. Since the rivets 33 are designed as countersunk rivets, they do not interfere with the further assembly and in particular not with the pushing on of the flanges 45, 46 of the combustion chamber head 32.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Connection Of Plates (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)

Claims (10)

  1. Procédé de montage d'une chambre de combustion (15) d'un moteur de turbine à gaz, sachant qu'une paroi de chambre de combustion extérieure de forme annulaire (29) et une paroi de chambre de combustion intérieure de forme annulaire (30) sont mises en position l'une par rapport à l'autre et reliées par une plaque frontale (31) et sachant qu'une tête de chambre de combustion (32) est ensuite montée, caractérisé en ce que la plaque frontale (31) est reliée à ladite paroi de chambre de combustion extérieure (29) et à ladite paroi de chambre de combustion intérieure (30) par des rivets (33) répartis sur la circonférence et que la tête de chambre de combustion (32) est mise ensuite en position et vissée à l'agencement de la plaque frontale (31), la paroi de chambre de combustion extérieure (29) et la paroi de chambre de combustion intérieure (30) au moyen de boulons filetés (34) et d'écrous (35), ledit agencement étant prémonté au moyen de rivets (33).
  2. Procédé selon la revendication n° 1, caractérisé en ce que la paroi de chambre de combustion extérieure (29), la paroi de chambre de combustion intérieure (30) et la plaque frontale (31) sont pourvues, avant le montage, d'une multitude d'évidements pour rivets (36) alignés les uns par rapport aux autres à l'état monté et répartis sur la circonférence.
  3. Procédé selon la revendication n° 2, caractérisé en ce que les évidements pour rivets (36) sont conçus sous forme de trous circulaires ou de trous oblongs.
  4. Procédé selon la revendication n° 2 ou n° 3, caractérisé en ce que la rivure n'a lieu que sur quelques-uns des évidements pour rivets (36).
  5. Procédé selon une des revendications n° 1 à n° 4, caractérisé en ce que sont utilisés comme rivets (33) des rivets à tête noyée.
  6. Procédé selon une des revendications n° 1 à n° 5, caractérisé en ce que les rivets (33) sont répartis uniformément sur la circonférence.
  7. Procédé selon une des revendications n° 2 à n° 6, caractérisé en ce que la tête de chambre de combustion (32) est pourvue d'une multitude d'évidements pour vis (37) qui sont alignés à l'état monté avec les évidements pour vis de la paroi de chambre de combustion extérieure (29), de la paroi de chambre de combustion intérieure (30) et de la plaque frontale (31).
  8. Procédé selon une des revendications n° 1 à n° 7, caractérisé en ce qu'avant le montage de la plaque frontale (31), au moins un écran thermique (38) est fixé à celle-ci au moyen de boulons filetés (39) et d'écrous (40).
  9. Procédé selon une des revendications n° 1 à n° 8, caractérisé en ce que sont disposés en alternance, répartis sur la conférence, des évidements pour vis (37) et des évidements pour rivets (36).
  10. Procédé selon une des revendications n° 1 à n° 9, caractérisé en ce que la paroi de chambre de combustion extérieure (29) et/ ou la paroi de chambre de combustion intérieure (30) et/ ou la plaque frontale (31) et/ ou la tête de chambre de combustion (32) sont (est) fabriquée(s) d'un matériau de tôle.
EP16202400.4A 2015-12-11 2016-12-06 Procédé de montage d'une chambre de combustion d'une turbine à gaz Not-in-force EP3179169B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102015224990.5A DE102015224990A1 (de) 2015-12-11 2015-12-11 Verfahren zur Montage einer Brennkammer eines Gasturbinentriebwerks

Publications (2)

Publication Number Publication Date
EP3179169A1 EP3179169A1 (fr) 2017-06-14
EP3179169B1 true EP3179169B1 (fr) 2018-01-31

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP16202400.4A Not-in-force EP3179169B1 (fr) 2015-12-11 2016-12-06 Procédé de montage d'une chambre de combustion d'une turbine à gaz

Country Status (3)

Country Link
US (1) US10544942B2 (fr)
EP (1) EP3179169B1 (fr)
DE (1) DE102015224990A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110594268B (zh) * 2019-09-20 2021-01-26 西安聚行机电科技发展有限公司 一种干涉配合无铆托板螺母的安装和拆卸方法

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DE19643028A1 (de) * 1996-10-18 1998-04-23 Bmw Rolls Royce Gmbh Brennkammer einer Gasturbine mit einem ringförmigen Kopfabschnitt
DE10048864A1 (de) * 2000-10-02 2002-04-11 Rolls Royce Deutschland Brennkammerkopf für eine Gasturbine
US6449952B1 (en) 2001-04-17 2002-09-17 General Electric Company Removable cowl for gas turbine combustor
FR2891351B1 (fr) * 2005-09-23 2007-12-07 Snecma Chambre de combustion de moteur a turbine a gaz avec carenage
FR2897144B1 (fr) * 2006-02-08 2008-05-02 Snecma Sa Chambre de combustion de turbomachine a fentes tangentielles
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Also Published As

Publication number Publication date
US20170167731A1 (en) 2017-06-15
US10544942B2 (en) 2020-01-28
EP3179169A1 (fr) 2017-06-14
DE102015224990A1 (de) 2017-06-14

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