EP1707758B1 - Elément de coque pour chambre combustion et chambre combustion - Google Patents

Elément de coque pour chambre combustion et chambre combustion Download PDF

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Publication number
EP1707758B1
EP1707758B1 EP05006399A EP05006399A EP1707758B1 EP 1707758 B1 EP1707758 B1 EP 1707758B1 EP 05006399 A EP05006399 A EP 05006399A EP 05006399 A EP05006399 A EP 05006399A EP 1707758 B1 EP1707758 B1 EP 1707758B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
shell element
chamber shell
holes
flange
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
EP05006399A
Other languages
German (de)
English (en)
Other versions
EP1707758A1 (fr
Inventor
Dr. Andreas Böttcher
Peter Danyluk
Claus Krusch
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
Original Assignee
Siemens AG
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 filed Critical Siemens AG
Priority to ES05006399T priority Critical patent/ES2368717T3/es
Priority to EP05006399A priority patent/EP1707758B1/fr
Priority to AT05006399T priority patent/ATE522703T1/de
Publication of EP1707758A1 publication Critical patent/EP1707758A1/fr
Application granted granted Critical
Publication of EP1707758B1 publication Critical patent/EP1707758B1/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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation

Definitions

  • the present invention relates to a combustion chamber shell element for constructing a combustion chamber together with at least one further combustion chamber shell element.
  • the invention relates to a combustor constructed from combustion chamber shell elements.
  • the invention relates to a combustion chamber outer shell element for constructing the combustion chamber outer shell of an annular combustion chamber for a gas turbine plant.
  • Such a combustion chamber shell element is made EP 1 429 077 A1 known.
  • Combustion chambers for example combustion chambers for gas turbine plants, generally comprise a combustion chamber shell with a heat shield upstream of the combustion chamber shell toward the interior of the combustion chamber.
  • flow channels are arranged between the combustion chamber shell and the heat shields through which a cooling fluid for cooling the combustion chamber shell and the heat shield elements flows, which is previously conducted past the outside of the combustion chamber shell.
  • the aim here is to achieve a homogeneous temperature distribution in the entire combustion chamber shell in order to avoid mechanical stresses due to temperature inhomogeneities.
  • the first object is achieved by a combustion chamber shell element according to claim 1 and the second object by a combustion chamber according to claim 8.
  • the dependent claims contain advantageous developments of the invention.
  • An inventive combustion chamber shell element for constructing a combustion chamber together with at least one further combustion chamber shell element has at least one connection region with receiving recesses for receiving connecting elements, which are provided for establishing the connection with another combustion chamber shell element.
  • the connection area has further recesses which are not provided for receiving connecting elements.
  • connection region can be influenced by means of the further recesses. Both variables have a direct influence on the mechanical stresses occurring in transient states of the gas turbine plant in the connection region and in the regions of the combustion chamber shell adjacent to the connection region.
  • the elasticity of the connecting region can be increased, which counteracts mechanical stresses.
  • Additional recesses formed as holes may increase the surface area of the connection area and thus provide even heating or cooling of the connection area in transient gas turbine conditions.
  • the additional holes may have the same opening dimensions as the through-holes. The through holes and the additional holes can then be made with the same tool.
  • the combustion chamber shell element can have at least one flange as connection region, wherein the receiving recesses and the further recesses are arranged in the flange.
  • the combustion chamber shell element is designed as a half shell and has a structure which makes it possible to build up the combustion chamber outer shell of a combustion chamber in cooperation with a second combustion chamber shell element likewise designed as a half shell.
  • the combustion chamber shell element according to the invention can in particular be configured as a combustion chamber shell element for constructing the combustion chamber outer shell of an annular combustion chamber of a gas turbine plant.
  • the invention also provides a combustion chamber, in particular a combustion chamber for a gas turbine plant, which has an outer shell constructed from at least two combustion chamber shell elements according to the invention.
  • the combustion chamber can be designed in particular as an annular combustion chamber.
  • FIG. 1 shows by way of example a gas turbine 100 in a longitudinal partial section.
  • the gas turbine 100 has inside a rotatably mounted about a rotation axis 102 rotor 103, which is also referred to as a turbine runner.
  • a compressor 105 for example, a toroidal combustion chamber 110, in particular annular combustion chamber 106, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
  • the annular combustion chamber 106 communicates with an annular annular hot gas channel 111, for example.
  • annular annular hot gas channel 111 for example.
  • turbine stages 112 connected in series form the turbine 108.
  • Each turbine stage 112 is formed, for example, from two blade rings. In the flow direction of a working medium As can be seen in the hot gas duct 111 of a guide blade row 115, a row 125 formed of rotor blades 120 follows.
  • the guide vanes 130 are fastened to an inner housing 138 of a stator 143, whereas the moving blades 120 of a row 125 are attached to the rotor 103 by means of a turbine disk 133, for example.
  • air 105 is sucked in and compressed by the compressor 105 through the intake housing 104.
  • the compressed air provided at the turbine-side end of the compressor 105 is supplied to the burners 107 where it is mixed with a fuel.
  • the mixture is then burned to form the working fluid 113 in the combustion chamber 110.
  • the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120.
  • the working medium 113 expands in a pulse-transmitting manner so that the rotor blades 120 drive the rotor 103 and drive the machine coupled to it.
  • the components exposed to the hot working medium 113 are subject to thermal loads during operation of the gas turbine 100.
  • the guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the direction of flow of the working medium 113, are subjected to the greatest thermal stress in addition to the heat shield bricks lining the annular combustion chamber 106.
  • the guide vane 130 has a guide vane foot (not shown here) facing the inner housing 138 of the turbine 108 and a vane foot opposite Guide vane head on.
  • the vane head faces the rotor 103 and fixed to a mounting ring 140 of the stator 143.
  • the FIG. 2 shows a combustion chamber 110 of a gas turbine.
  • the combustion chamber 110 is configured, for example, as a so-called annular combustion chamber, in which a plurality of burners 107 arranged around the rotation axis 102 in the circumferential direction open into a common combustion chamber space.
  • the combustion chamber 110 is configured in its entirety as an annular structure, which is positioned around the axis of rotation 102 around.
  • the combustion chamber 110 is designed for a comparatively high temperature of the working medium M of about 1000 ° C to 1600 ° C.
  • the combustion chamber wall 153 is provided on its side facing the working medium M side with an inner lining formed from heat shield elements 155.
  • Each heat shield element 155 is equipped on the working medium side with a particularly heat-resistant protective layer or made of high-temperature-resistant material. These may be solid ceramic stones or alloys with MCrA1X and / or ceramic coatings. The materials of the combustion chamber wall and its coatings may be similar to the turbine blades.
  • Due to the high temperatures inside the combustion chamber 110 may also be provided for the heat shield elements 155 and for their holding elements, a cooling system.
  • FIG. 3 is shown as an embodiment of the invention, a section of a combustion chamber shell element 1, which is designed to construct the outer shell of an annular combustion chamber 110 of a gas turbine plant 100.
  • the Combustor outer shell substantially corresponds to the in Fig. 2 illustrated combustion chamber wall.
  • the combustion chamber shell element 1 is designed as a half shell which, together with a further half shell, forms the combustion chamber outer shell of the annular combustion chamber 110.
  • each combustion chamber shell element 1 has a flange 3, in which through-holes 5, 5 'are arranged, which serve as receiving recesses for screws (not shown).
  • the two combustion chamber shell elements can be screwed together to form the combustion chamber shell.
  • the flanges 3 of the two combustion chamber shell elements are in contact via contact surfaces 2.
  • the through holes 5, 5 'each have an opening diameter which is suitable for receiving the screw shafts.
  • the opening diameter of the through holes 5, 5 ' is widened in order to accommodate screw heads or nuts at least partially.
  • the flange 3 extends in the axial direction of the combustor 110 to be constructed and has a widened section 7 at its ends. A portion of the through holes 5 is disposed in the wide sections 7, another part of the through holes 5 'is located in the narrow section 9. There, where in the narrow section 9, the through holes. 5 'are arranged, the flange 3 has slots 10 which extend from the outer surface 11 of the flange 3 to the through holes 5' and open into this. The slots 10 increase the elasticity of the flange, so that impediments of temperature-induced expansions of the flange 3 are reduced. Due to the increased elasticity becomes an uneven expansion less resistance to the flange material than would be the case without the slots 10.
  • blind bores 13 are arranged in the flange, which also extend through the flange 3 and have substantially the same opening diameter as the through bores 5, 5'.
  • the blind bores 13 do not serve to accommodate screw shanks. Since no screw head or no nut is to be received, the opening diameter of the blind holes 13 in the region of the upper side 4 of the flange 3 is not widened as the opening diameter of the through holes 5, 5 '.
  • the flange has slots 15 which extend from the outside 11 of the flange to the blind bores 13 and open into them. Like the slots 10, the slots 15 serve to increase the elasticity of the flange.
  • a more uniform temperature distribution in the flange is achieved during transient gas turbine conditions.
  • the uniform temperature distribution in the flange 3 results from the larger surface that provides the flange due to the blind holes for contact with a heating and cooling medium.
  • a uniform distribution of the blind bores 13 via the flange 3 leads to a comparatively uniform heating or cooling of the flange 3 during transient gas turbine states.
  • the flange 3 heats up rather unevenly when the measures according to the invention are not taken.
  • This compressed air is preheated, on the one hand by the compression process itself and, on the other hand, optionally by an air preheating device which extracts heat from the gas turbine exhaust gases and transfers this heat to the compressed air.
  • the preheating The compressed air by means of such a preheater may be advantageous in terms of efficiency and pollutant emissions of the gas turbine plant. Since the preheated air, even if a preheating device is used, is significantly cooler than the combustion exhaust gases, the preheated air from the compressor is used for cooling the combustion chamber components. It flows around the combustion chamber outer shell and passes through inlet openings 17, which are present in the combustion chamber shell elements 1, therethrough.
  • the preheated air is warmer than the combustion chamber shell elements 1, so that it leads to a heating of the combustion chamber shell elements 1 in the first minutes of starting the gas turbine plant 100.
  • the blind bores 13 increase the area available for heat transfer from the preheated compressor air to the flange 3, so that the flange heats up more uniformly.
  • the slots 10, 15 contribute to an increase in the area and thus to a more uniform heating.

Landscapes

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

Claims (9)

  1. Elément ( 1 ) de coque de chambre de combustion pour la construction d'une chambre de combustion ( 110 ) annulaire en section transversale ensemble au moins avec un autre élément ( 1 ) de coque de chambre de combustion, dans lequel chaque élément ( 1 ) de coque de chambre de combustion a au moins une zone ( 3 ) de liaison du côté du bord ayant des évidements ( 5, 5' ) de réception pour la réception d'éléments de liaison, qui sont prévus pour la production de la liaison avec l'un des autres éléments de coque de chambre de combustion,
    caractérisé en ce que
    la zone ( 3 ) de liaison de l'élément ( 1 ) de coque de chambre de combustion a, en plus des évidements ( 5, 5' ) de réception pour augmenter l'élasticité, d'autres évidements ( 10, 13, 15 ) qui ne sont pas prévus pour la réception d'éléments de réception.
  2. Elément ( 1 ) de coque de chambre de combustion suivant la revendication 1,
    caractérisé en ce que
    il est formé comme zone de liaison au moins une bride ( 3 ) et les évidements ( 5, 5' ) de réception, ainsi que les autres évidements ( 10, 13, 15 ) sont ménagés dans la bride ( 3 ).
  3. Elément ( 1 ) de coque de chambre de combustion suivant la revendication 1 ou 2,
    caractérisé en ce que
    les autres évidements sont constitués sous la forme de fentes ( 10, 15 ) dans la zone ( 3 ) de liaison.
  4. Elément ( 1 ) de coque de chambre de combustion suivant la revendication 1, 2 ou 3,
    caractérisé en ce que
    les autres évidements sont conformés sous la forme de trous ( 13 ) dans la zone ( 3 ) de liaison.
  5. Elément ( 1 ) de coque de chambre de combustion suivant la revendication 4,
    caractérisé en ce que
    les évidements de réception sont formés sous la forme de trous ( 5, 5' ) traversants et les trous ( 13 ) ont les mêmes dimensions d'ouverture que les trous ( 5, 5' ) traversant.
  6. Elément ( 1 ) de coque de chambre de combustion suivant l'une des revendications précédentes,
    caractérisé par
    sa conformation en hémicoque pour la construction d'une coque extérieure de chambre de combustion ensemble avec un deuxième élément ( 1 ) de coque de chambre de combustion constitué en hémicoque.
  7. Elément ( 1 ) de coque de chambre de combustion suivant l'une des revendications précédentes,
    caractérisé par
    sa conformation sous la forme d'un élément ( 1 ) de coque de chambre de combustion pour la construction de la coque extérieure de chambre de combustion d'une chambre de combustion ( 110 ) annulaire.
  8. Chambre de combustion ( 110 ), notamment pour une installation de turbine à gaz,
    caractérisée en ce que
    elle a une coque extérieure, qui est constituée d'au moins deux éléments ( 1 ) de coque de chambre de combustion suivant l'une des revendications 1 à 7.
  9. Chambre de combustion ( 110 ) suivant la revendication 8,
    caractérisée par
    sa conformation en chambre de combustion annulaire d'une installation de turbine à gaz.
EP05006399A 2005-03-23 2005-03-23 Elément de coque pour chambre combustion et chambre combustion Not-in-force EP1707758B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
ES05006399T ES2368717T3 (es) 2005-03-23 2005-03-23 Elemento de cáscara de cámara de combustión y cámara de combustión.
EP05006399A EP1707758B1 (fr) 2005-03-23 2005-03-23 Elément de coque pour chambre combustion et chambre combustion
AT05006399T ATE522703T1 (de) 2005-03-23 2005-03-23 Brennkammerschalenelement und brennkammer

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP05006399A EP1707758B1 (fr) 2005-03-23 2005-03-23 Elément de coque pour chambre combustion et chambre combustion

Publications (2)

Publication Number Publication Date
EP1707758A1 EP1707758A1 (fr) 2006-10-04
EP1707758B1 true EP1707758B1 (fr) 2011-08-31

Family

ID=34934463

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05006399A Not-in-force EP1707758B1 (fr) 2005-03-23 2005-03-23 Elément de coque pour chambre combustion et chambre combustion

Country Status (3)

Country Link
EP (1) EP1707758B1 (fr)
AT (1) ATE522703T1 (fr)
ES (1) ES2368717T3 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20180223691A1 (en) * 2017-02-03 2018-08-09 United Technologies Corporation Case flange with stress reducing features

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6352404B1 (en) * 2000-02-18 2002-03-05 General Electric Company Thermal control passages for horizontal split-line flanges of gas turbine engine casings
US6691019B2 (en) * 2001-12-21 2004-02-10 General Electric Company Method and system for controlling distortion of turbine case due to thermal variations
EP1429077B1 (fr) * 2002-12-10 2008-07-30 Siemens Aktiengesellschaft Turbine à gaz

Also Published As

Publication number Publication date
ATE522703T1 (de) 2011-09-15
EP1707758A1 (fr) 2006-10-04
ES2368717T3 (es) 2011-11-21

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