EP1443275B1 - Chambre de combustion - Google Patents

Chambre de combustion Download PDF

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Publication number
EP1443275B1
EP1443275B1 EP03001890A EP03001890A EP1443275B1 EP 1443275 B1 EP1443275 B1 EP 1443275B1 EP 03001890 A EP03001890 A EP 03001890A EP 03001890 A EP03001890 A EP 03001890A EP 1443275 B1 EP1443275 B1 EP 1443275B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
wall
cooling medium
coolant
heat shield
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.)
Expired - Lifetime
Application number
EP03001890A
Other languages
German (de)
English (en)
Other versions
EP1443275A1 (fr
Inventor
Paul-Heinz Jeppel
Wilhelm Schulten
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.)
Siemens AG
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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 Siemens AG, Siemens Corp filed Critical Siemens AG
Priority to ES03001890T priority Critical patent/ES2307834T3/es
Priority to EP03001890A priority patent/EP1443275B1/fr
Priority to DE50310313T priority patent/DE50310313D1/de
Priority to CNB2004100020853A priority patent/CN100393997C/zh
Priority to JP2004013771A priority patent/JP2004340564A/ja
Priority to US10/767,677 priority patent/US7082771B2/en
Publication of EP1443275A1 publication Critical patent/EP1443275A1/fr
Application granted granted Critical
Publication of EP1443275B1 publication Critical patent/EP1443275B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F23R3/005—Combined with pressure or heat exchangers
    • 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
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies

Definitions

  • the invention relates to a combustion chamber for a gas turbine whose combustion chamber is bounded by an annular outer wall on the one hand and an annular inner wall arranged therein on the other hand.
  • the combustion chamber walls are provided on the inside with a lining formed by a number of heat shield elements, wherein the or each heat shield element forms an interior that can be acted upon by a coolant.
  • the invention further relates to a gas turbine with such a combustion chamber.
  • Combustion chambers are part of gas turbines that are used in many areas to drive generators or work machines.
  • the energy content of a fuel is used to generate a rotational movement of a turbine shaft.
  • the fuel is burned to burners in their downstream combustion chambers, wherein compressed air is supplied by an air compressor.
  • the combustion of the fuel produces a high pressure working fluid at a high temperature. This working fluid is fed into a turbine unit downstream of the combustion chambers, where it relaxes to perform work.
  • each burner can be assigned a separate combustion chamber, wherein the working medium flowing out of the combustion chambers can be brought together before or in the turbine unit.
  • the combustion chamber can also be designed in a so-called annular combustion chamber design, in which a plurality, in particular all, of the burner open into a common, usually annular combustion chamber.
  • the turbine unit adjoining the combustion chamber in the flow direction of the working medium usually comprises a turbine shaft which is provided with a number of rotatable blades connected, forming the annular blade rows.
  • the turbine unit comprises a number of stationary vanes, which are also fixed in a ring shape with the formation of rows of vanes on the inner casing of the turbine.
  • the blades serve to drive the turbine shaft by momentum transfer of the working fluid flowing through the turbine unit, while the guide vanes serve to guide the flow of the working medium between two successive blade rows or blade rows seen in the flow direction of the working medium.
  • the rotational movement of the turbine shaft is generally used to drive the air compressor upstream of the combustion chamber, it is extended beyond the turbine unit so that in the area of the annular combustion chamber upstream of the turbine, the turbine shaft is surrounded in a toroidal manner by the annular combustion chamber.
  • the combustion chamber is bounded by an annular outer wall on the one hand and an annular inner wall arranged therein on the other hand.
  • the inner wall of the combustion chamber consists of two or more individual parts, which are screwed together on their side facing the turbine shaft.
  • the combustion chamber wall can be lined on its inside with heat shield elements, which can be provided with particularly heat-resistant protective layers, and which are cooled by the actual combustion chamber wall therethrough.
  • a cooling method also known as "impingement cooling” can be used.
  • impingement cooling a coolant, as a rule cooling air, is supplied to the heat shield elements through a plurality of bores in the combustion chamber wall, so that the coolant bounces substantially perpendicularly onto its outer surface facing the combustion chamber wall.
  • the coolant heated by the cooling process is then removed from the interior, which forms the combustion chamber wall with the heat shield elements.
  • Such a configuration is made DE-A-1980568 known.
  • the above-described structure of the annular combustion chamber also has some other disadvantages with respect to maintenance work.
  • maintenance and repair work parts of the combustion chamber such as the heat shield elements or the cooling system used and in particular also components of the downstream turbine unit must be repaired or replaced due to the high thermal and mechanical stress.
  • a disadvantage of the construction of the combustion chamber is that the turbine shaft is not accessible from the combustion chamber during maintenance. Thus, for maintenance work on the turbine shaft in the region of the annular combustion chamber or for repairs to the first guide vanes and rotor blades directly adjoining the combustion chamber, generally all the adjoining vanes and guide vanes of the turbine unit must be removed.
  • the invention is therefore based on the object to provide a combustion chamber of the type mentioned above, which is suitable for comparatively simple construction for a particularly high system efficiency and in which the inner wall of the combustion chamber is comparatively quickly and easily disassembled.
  • the object is achieved according to the invention by arranging a number of coolant distributors in the respective heat shield element associated with each interior space, and by forming the inner wall of the combustion chamber from a number of wall elements fastened on a supporting structure of the inner wall, wherein the support structure of a Number of pieces abutting on a horizontal parting line sections is formed, which are connected to each other in the region of the parting line via a number of obliquely aligned with the inner wall surface screw.
  • the invention is based on the consideration that for a particularly high system efficiency, a reliable and in particular comprehensive coverage of the heat shield elements should be ensured with coolant. Even with consistent compliance with this requirement, the expenditure on equipment and in particular the production cost can be kept low by the variety of hitherto provided coolant holes are replaced by a simplified system.
  • the invention is based on the consideration that the attachment of the various wall elements of the combustion chamber inner wall to each other should be accessible from the combustion chamber and the combustion chamber inner wall is therefore also to be dismantled therefrom.
  • the various support structure elements of the combustion chamber inner wall which abut each other at their horizontal parting line, should be connected to each other by a fastening, which by a vertical force on the parting line connects with each other.
  • each threaded connection is expediently assigned a key.
  • the feather key avoids that the support structure elements bolted to one another on the horizontal parting line are displaced relative to one another by the horizontal force component of the screw connection.
  • the feather key advantageously runs along the horizontal parting line and is fitted snugly into grooves of the abutting support structure elements, so that they can not move against each other, and preferably only the vertical force component of the screw connection on the horizontal parting line required for fastening the screw connection occurs.
  • a coolant supply line is connected in each case via a coolant distributor to a number of coolant outlet openings.
  • the heat shields located directly in front of the coolant distributors can be cooled by impingement cooling.
  • the outlet openings of the coolant distributor are expediently dimensioned such that the sum of their cross-sectional areas of all outlet openings is smaller than the cross section of the coolant supply line.
  • the coolant heated after the cooling process is expediently discharged through bores in the combustion chamber wall from the interior space between the heat shields and the combustion chamber wall into a coolant discharge system. Due to the shape and a suitable arrangement of the coolant manifold, which ensures a sufficient distance of the coolant manifolds from each other, the heated cooling air can flow through the spaces between the coolant manifolds through to the located on the combustion chamber wall openings of the holes.
  • the return bores are preferably uniformly distributed over the entire length of the combustion chamber in constant proportion to the number of coolant distributors, so that the coolant can be uniformly discharged in all return bores with an approximately equal return temperature.
  • heat shield elements are preferably formed at their edges in such a way that, through a double bend, they form an anchorage in the combustion chamber, which can be anchored in a recess of the combustion chamber wall which forms the groove and thus fastened.
  • the recess in the combustion chamber wall is summarized for adjacent heat shield elements, so that adjacent heat shield elements abut each other at their, resulting from the bending end face, and thus constitute a seal for the combustion chamber and the working medium flowing therein.
  • the abovementioned combustion chamber is preferably part of a gas turbine.
  • the advantages achieved by the invention are in particular that a large-scale and comprehensive loading of the heat shield elements with coolant is made possible by the use of coolant manifolds even with low production costs.
  • the coolant pressure loss can be kept low during the cooling of the combustion chamber, so that thus increases the system efficiency of the combustion chamber.
  • the low coolant pressure loss can also be achieved, in particular, because the cooling air distributors require only a few supply bores in the combustion chamber wall.
  • the use of a number of coolant distributors can ensure uniform cooling with low coolant pressure loss, since in the case of coolant supply via a coolant distributor, the coolant branches off from a larger coolant supply line into a plurality of smaller coolant outlet openings only shortly before impingement cooling at the heat shield elements. This ensures that the coolant flows through only a short distance with a relatively small cross-section, so that the coolant pressure loss is limited.
  • the abovementioned combustion chamber is preferably part of a gas turbine.
  • the gas turbine 1 has a compressor 2 for combustion air, a combustion chamber 4 and a turbine 6 for driving the compressor 2 and a generator, not shown, or a working machine.
  • the turbine 6 and the compressor 2 are arranged on a common, also called turbine rotor turbine shaft 8, with which the generator or the working machine is connected, and which is rotatably mounted about its central axis 9.
  • the running in the manner of an annular combustion chamber 4 is equipped with a number of burners 10 for the combustion of a liquid or gaseous fuel.
  • the turbine 6 has a number of rotatable blades 12 connected to the turbine shaft 8.
  • the blades 12 are arranged in a ring on the turbine shaft 8 and thus form a number of blade rows.
  • the turbine 6 comprises a number of fixed vanes 14, which are also fixed in a ring shape with the formation of rows of vanes on an inner casing 16 of the turbine 6.
  • the blades 12 serve to drive the turbine shaft 8 by momentum transfer from the turbine 6 flowing through the working medium M.
  • the vanes 14, however, serve to guide the flow of the working medium M between two seen in the flow direction of the working medium M consecutive blade rows or blade rings.
  • a successive pair of a ring of vanes 14 or a row of vanes and a ring of blades 12 or a blade row is also referred to as a turbine stage.
  • Each vane 14 has a platform 18, also referred to as a blade root, which is arranged to fix the respective vane 14 on the inner housing 16 of the turbine 6 as a wall element.
  • the platform 18 is a thermally comparatively heavily loaded component which forms the outer boundary of a heating gas channel for the working medium M flowing through the turbine 6.
  • Each blade 12 is attached to the turbine shaft 8 in an analogous manner via a platform 20, also referred to as a blade root.
  • each guide ring 21 on the inner housing 16 of the turbine 6 is arranged between the spaced-apart platforms 18 of the guide vanes 14 of two adjacent rows of guide vanes.
  • the outer surface of each guide ring 21 is also exposed to the hot, the turbine 6 flowing through the working medium M and spaced in the radial direction from the outer end 22 of the blade 12 opposite him through a gap.
  • the arranged between adjacent rows of guide blades guide rings 21st serve in particular as cover elements, which protects the inner wall or other housing-mounting parts from thermal overload by the hot working medium M flowing through the turbine 6.
  • the combustion chamber 4 is designed in the embodiment as a so-called annular combustion chamber, in which a plurality of circumferentially around the turbine shaft 8 arranged around burners 10 open into a common combustion chamber space.
  • the combustion chamber 4 is configured in its entirety as an annular structure which is positioned around the turbine shaft 8 around.
  • combustion chamber 4 shown in section, which continues toroidally around the turbine shaft 8 around.
  • the combustion chamber 4 has an initial or inflow section, into which the outlet of the respective associated burner 10 terminates.
  • Viewed in the flow direction of the working medium M then narrows the cross section of the combustion chamber 4, wherein the self-adjusting flow profile of the working medium M is taken into account in this space area.
  • the combustion chamber 24 of the combustion chamber 4 is bounded by a combustion chamber wall 25 which is formed on the one hand by an annular combustion chamber outer wall 26 and on the other hand by an annular combustion chamber inner wall 28 disposed therein.
  • the combustion chamber 4 is designed to be able to remove the combustion chamber inner wall 28 in a particularly simple manner, for example for maintenance work, in order to gain access to the combustion chamber inner wall 28 surrounded turbine shaft 8 and the combustion chamber 4 immediately adjacent blades 12 and vanes 14 of the turbine 6 to receive.
  • the combustion chamber inner wall 28 consists of two wall elements 30, which are joined together to form a substantially horizontally extending parting line 31 to the combustion chamber inner wall 28.
  • the combustion chamber 4 is in particular designed to be able to disassemble the wall elements 30 of the combustion chamber inner wall 28 from the combustion chamber 24. These are, as in FIG. 4 is shown in section, the wall elements 30 connected to the horizontal parting line 31 formed by them with obliquely to the inner surface of the combustion chamber inner wall 28 extending screw 32.
  • each screw connection 32 comprises a screw 33 guided essentially obliquely to the surface formed by the combustion chamber inner wall 28, which cooperates with a thread 34 incorporated in one of the wall elements 30.
  • the wall elements 30 do not move against each other by the resulting due to the oblique to the combustion chamber inner wall 28 screws 33 horizontal force component, the screw 32 is assigned a key 35. This extends in a position close to the respective screw connection 32 along the horizontal parting line 31 of the wall elements 30 and is fitted in grooves of the wall elements 30 of the combustion chamber inner wall 28.
  • the combustion chamber 4 is designed for a comparatively high temperature of the working medium M of about 1200 ° C to 1500 ° C.
  • the combustion chamber wall 25, as in FIG. 5 illustrated provided on its side facing the working medium M side with a lining formed from heat shield elements 38.
  • Each heat shield element 38 is working medium side with a particularly heat-resistant protective layer. Due to the high temperatures inside the combustion chamber 4, a cooling system is also provided for the heat shield elements 38.
  • the cooling system is based on the principle of impingement cooling, in which cooling air K is blown as coolant under sufficiently high pressure at a plurality of points to the component to be cooled.
  • the cooling system is designed with a simple structure for a reliable, full coverage of the heat shield elements 38 with cooling air and also for a particularly low coolant pressure loss.
  • the heat shield elements 38 are cooled from their outside by the cooling air K, which is passed through a number of arranged in the respective heat shield element 38 and the combustion chamber wall 25 interior 40 arranged coolant manifolds 42 on the surface of the respective heat shield element 38.
  • FIG. 5 a section of the combustion chamber wall 25 is shown.
  • a number of the coolant distributors 42 are distributed over the entire surface of the respective heat shield element 38 in order to ensure a uniform cooling.
  • the coolant K flows through an associateddestoffzuclasstechnisch 44 in the respective coolant distributor 42.
  • the coolant K is passed through a number of coolant outlet openings 46 on the surface of the heat shield element 38 where it is cooled by the coolant K by impingement cooling.
  • the heat shield elements 38 are attached to the combustion chamber wall 28 in a space-saving manner for the attached cooling system and the partial joint connection.
  • a system with tongue and groove is used.
  • the heat shield elements 38 are formed at their edges in such a way that, through a double bend, they form an anchorage in the direction of the combustion chamber, which can be anchored in a recess in the combustion chamber wall 25 which forms the groove and fastened therewith.
  • adjacent heat shield elements 38 are attached to combined grooves that they touch each other and so seal the combustion chamber 24 of the combustion chamber 4.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (7)

  1. Chambre de combustion (4) pour une turbine (1) à gaz, dont l'espace (24) de combustion est délimité par une paroi (28) intérieure annulaire de chambre de combustion et par une paroi (26) extérieure de combustion, qui sont munis du côté intérieur d'un garnissage formé d'un certain nombre d'éléments (38) de bouclier thermique, le ou chaque élément (38) de bouclier thermique formant avec la paroi de la chambre de combustion un espace (40) intérieure pouvant être alimenté en un fluide (K) de refroidissement, espace dans lequel est disposé un répartiteur (42) de fluide de refroidissement, et dans laquelle la paroi (28) intérieure de la chambre de combustion est formée d'un certain nombre d'éléments (30) de paroi aboutés en des sous-joints (31) horizontaux, caractérisée en ce que les éléments de paroi sont assemblés entre eux dans la partie des sous- joints (31) par un certain nombre de vissages (32) inclinés par rapport à la surface de la paroi intérieure.
  2. Chambre de combustion (4) suivant la revendication 1, dans laquelle une clavette (35) est associée au vissage ou à chaque vissage (32).
  3. Chambre de combustion (4) suivant la revendication 1, dans laquelle un conduit (44) d'apport de fluide de refroidissement communique avec une multiplicité d'ouvertures (46) de sortie de fluide de refroidissement par un répartiteur (42) de fluide de refroidissement.
  4. Chambre de combustion (4) suivant la revendication 1 à 3, dans laquelle les ouvertures (46) de sortie du fluide de refroidissement ont des dimensions telles que la somme des surfaces des sections transversales de toutes les ouvertures (46) de sortie du fluide de refroidissement d'un répartiteur (42) de fluide de refroidissement est plus petite que la surface de section transversale du conduit (44) associé d'apport de fluide de refroidissement.
  5. Chambre de combustion (4) suivant l'une des revendications 1 à 4, dans laquelle l'espace (40) intérieure ou chaque espace (40) intérieur communique avec un système d'évacuation de fluide de refroidissement par un certain nombre de trous.
  6. Chambre de combustion (4) suivant la revendication 1, dans laquelle les éléments (38) de bouclier thermique sont fixés par un système à tenons et mortaises à la paroi (28) intérieure de la chambre de combustion ou à la paroi (26) extérieure de la chambre de combustion.
  7. Turbine (1) à gaz ayant une chambre de combustion (4) selon l'une des revendications 1 à 5.
EP03001890A 2003-01-29 2003-01-29 Chambre de combustion Expired - Lifetime EP1443275B1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
ES03001890T ES2307834T3 (es) 2003-01-29 2003-01-29 Camara de combustion.
EP03001890A EP1443275B1 (fr) 2003-01-29 2003-01-29 Chambre de combustion
DE50310313T DE50310313D1 (de) 2003-01-29 2003-01-29 Brennkammer
CNB2004100020853A CN100393997C (zh) 2003-01-29 2004-01-12 燃烧室
JP2004013771A JP2004340564A (ja) 2003-01-29 2004-01-22 燃焼器
US10/767,677 US7082771B2 (en) 2003-01-29 2004-01-29 Combustion chamber

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP03001890A EP1443275B1 (fr) 2003-01-29 2003-01-29 Chambre de combustion

Publications (2)

Publication Number Publication Date
EP1443275A1 EP1443275A1 (fr) 2004-08-04
EP1443275B1 true EP1443275B1 (fr) 2008-08-13

Family

ID=32605266

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03001890A Expired - Lifetime EP1443275B1 (fr) 2003-01-29 2003-01-29 Chambre de combustion

Country Status (6)

Country Link
US (1) US7082771B2 (fr)
EP (1) EP1443275B1 (fr)
JP (1) JP2004340564A (fr)
CN (1) CN100393997C (fr)
DE (1) DE50310313D1 (fr)
ES (1) ES2307834T3 (fr)

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US10823411B2 (en) 2017-02-23 2020-11-03 Raytheon Technologies Corporation Combustor liner panel end rail cooling enhancement features for a gas turbine engine combustor
US10830434B2 (en) 2017-02-23 2020-11-10 Raytheon Technologies Corporation Combustor liner panel end rail with curved interface passage for a gas turbine engine combustor
US10677462B2 (en) 2017-02-23 2020-06-09 Raytheon Technologies Corporation Combustor liner panel end rail angled cooling interface passage for a gas turbine engine combustor
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Also Published As

Publication number Publication date
JP2004340564A (ja) 2004-12-02
DE50310313D1 (de) 2008-09-25
EP1443275A1 (fr) 2004-08-04
US20040182085A1 (en) 2004-09-23
US7082771B2 (en) 2006-08-01
CN1519507A (zh) 2004-08-11
CN100393997C (zh) 2008-06-11
ES2307834T3 (es) 2008-12-01

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