EP2128524A1 - Bauteilanordnung, Brennkammeranordnung und Gasturbine - Google Patents

Bauteilanordnung, Brennkammeranordnung und Gasturbine Download PDF

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Publication number
EP2128524A1
EP2128524A1 EP08009563A EP08009563A EP2128524A1 EP 2128524 A1 EP2128524 A1 EP 2128524A1 EP 08009563 A EP08009563 A EP 08009563A EP 08009563 A EP08009563 A EP 08009563A EP 2128524 A1 EP2128524 A1 EP 2128524A1
Authority
EP
European Patent Office
Prior art keywords
groove
arrangement according
flame tube
component
combustion chamber
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.)
Ceased
Application number
EP08009563A
Other languages
German (de)
English (en)
French (fr)
Inventor
Christoph Cernay
Stefan Tschirren
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 EP08009563A priority Critical patent/EP2128524A1/de
Priority to JP2009125611A priority patent/JP5543132B2/ja
Priority to US12/471,534 priority patent/US20090288422A1/en
Publication of EP2128524A1 publication Critical patent/EP2128524A1/de
Ceased 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
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M2900/00—Special features of, or arrangements for combustion chambers
    • F23M2900/05002—Means for accommodate thermal expansion of the wall liner
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M2900/00—Special features of, or arrangements for combustion chambers
    • F23M2900/05005—Sealing means between wall tiles or panels
    • 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
    • F23R2900/00012—Details of sealing devices

Definitions

  • the present invention relates to a component assembly and a combustion chamber assembly with a sealing element. Moreover, the invention relates to a gas turbine.
  • a combustion chamber for example a combustion chamber of a gas turbine, often comprises various components which are partially pushed into one another.
  • the outlet of a flame tube and a transition element adjoining the flame tube are partially pushed into one another.
  • the typically resulting gap between the nested sections must be sealed. This is often done with the help of spring clamp seals, but can also be done by brush seals.
  • the pressure differential across the seal member produces a lateral thrust on the retainer ring which presses the ring against the side surface of a guide groove.
  • This thrust is basically desirable and even necessary because it reduces the leakage flow around the guide ring. If, in addition to the side surface of the ring and the contact surface of the guide groove have been processed smoothly and smoothly, this leakage is low.
  • the ring height and / or the pressure difference are relatively high, this can lead to frictional forces which practically block the retaining ring in the guide groove.
  • the components involved can be overloaded, which can lead to damage, for example, to a squashed brush, to deformation of the components or to cracks in the components.
  • the size of the ring can be reduced as much as possible.
  • several sealing rings can be used in series to reduce the pressure difference.
  • the friction can be reduced by smoothing and / or coating the surfaces involved.
  • these measures have been found to be insufficient for larger ring diameters and / or higher pressure differences.
  • the first object is achieved by a component arrangement according to claim 1.
  • the second object is achieved by a combustion chamber arrangement according to claim 12.
  • the third object is achieved by a gas turbine according to claim 19.
  • the dependent claims contain further, advantageous embodiments of the invention.
  • the component arrangement according to the invention comprises two component elements which, while leaving a gap, comprise sections which are pushed into one another and are arranged statically relative to one another.
  • the component assembly also includes a seal sealing the gap.
  • One of the two component elements has a groove which extends in the region of the gap to be sealed and which is open toward the other component element with a side surface.
  • the sealing element comprises a holding element having a first side surface and a second side surface.
  • the sealing element is at least partially disposed in the groove.
  • the first side surface of the holding member may be brought into abutment with the side surface of the groove by a pressure difference between a pressure acting on the first side surface and a pressure acting on the second side surface.
  • the side surface of the groove and / or the first side surface of the holding element comprise / comprises at least one pressure relief recess.
  • statically arranged relative to one another means that the component sections do not rotate relative to one another. Despite possible movements of the component sections according to the invention as a result of vibrations or thermal expansions, components which move in this way relative to one another are considered as being arranged statically relative to one another in the context of the invention.
  • groove can be understood in the context of the invention, in particular in the sense of a guide.
  • the pressure relief depression reduces the contact area of the abutting component elements. This reduces the area to which the applied pressure difference acts. This causes a reduction of the frictional force due to the reduced contact pressure and prevents blocking of the holding element and an overload of the elements involved.
  • the groove can be configured in particular as an annular groove.
  • the retaining element can be configured as a retaining ring.
  • the sealing element may be configured, for example, as a brush seal, which may in particular comprise a retaining ring with a brush.
  • the sealing element may comprise a cord seal, an open ring seal (C-ring) or a closed ring seal (O-ring).
  • the retaining ring with a cord seal, an open ring seal (C-ring) or a closed ring seal (O-ring) may be connected.
  • the sealing element may be designed as a pure piston ring or retaining ring.
  • the groove may continue to rotate around the component element to which it is open.
  • the pressure relief recess may extend along the entire side surface of the groove and / or along the entire first side surface (31 a) of the holding element.
  • multiple pressure relief pits may extend in the form of segments along the entire side surface of the groove and / or along the entire first side surface of the support member.
  • the pressure relief recess can thus be configured in other words as a circumferential groove or as a segmented groove. The segmentation results in an improved support of the retaining ring and thus an increased stability of the component assembly compared to an unsegmented designed pressure relief well.
  • the side surface of the groove and / or the first side surface of the holding element may / may be coated.
  • the friction between the adjoining side surfaces can also be reduced.
  • the pressure relief recess may in particular have a depth between 1 mm and 10 mm, preferably 1.5 mm.
  • One of the nested portions of the component elements may for example form the exit of a flame tube.
  • the outlet of the flame tube is arranged radially inward with respect to the telescoped portion of the other component element.
  • the gap can not be flowed through in the flow direction of the hot gas emerging from the flame tube, but only against the flow, which helps to reduce the leakage and allows the use of smaller seals compared to a gap, which can be flowed through in the flow direction.
  • the back of the inner member member is not wetted by the hot gas, whereby the heat load is reduced.
  • the amount of air required to rinse the gap is minimized.
  • one of the nested portions of the component elements may form a portion of a transition piece arranged between a combustor basket and a turbine inlet.
  • the section of the transition element is arranged radially outward relative to the nested section of the other component. Again, then only a flow through the gap against the general flow direction is possible.
  • the nested sections of the component elements may in particular be designed cylindrical.
  • component element may have the groove which comprises the radially outwardly arranged section with respect to the center axis of the sections pushed into one another.
  • that component element may also have the groove, which comprises the radially inwardly arranged section with respect to the center axis of the sections pushed into each other.
  • the combustion chamber arrangement comprises a flame tube with a flame tube outlet and a transition element downstream of the flame tube outlet in the flow direction of a hot gas emerging from the flame tube, with an inlet adapted to the flame tube outlet.
  • the Flammrohrausgang and the entrance of the transition element are partially pushed together.
  • a gap is formed between the flame tube outlet and the entrance of the transition element.
  • the flame tube exit or the transition element has an annular groove extending in the region of the gap to be sealed with a side surface.
  • the gap is sealed by a sealing element comprising a retaining element having a first side surface and a second side surface.
  • the sealing element is at least partially disposed in the groove.
  • the first side surface of the holding member may be abutted against the side surface of the groove by a pressure difference between a pressure acting on the first side surface and a pressure acting on the second side surface.
  • the side surface of the groove and / or the first side surface of the holding element comprise / comprises at least one pressure relief recess.
  • the pressure relief recess By the pressure relief recess, the contact surface of the abutting side surfaces of the groove and the holding element is reduced. This reduces the area to which the applied pressure difference acts. This causes a reduction in the frictional force and prevents blocking of the holding element and an overload of the components involved.
  • the side surface of the groove and / or the first side surface of the holding element may / may be coated. By choosing a suitable coating material, the friction between the adjoining side surfaces are also reduced.
  • the depressurization recess may have, for example, a depth between 1 mm and 10 mm, preferably 1.5 mm.
  • the groove can also be configured as an annular groove.
  • the sealing element may comprise, for example, a brush seal, a cord seal, an open ring seal (C-ring) or a closed ring seal (O-ring). In the case of a bush seal, this may in particular comprise a retaining ring with a brush. However, the sealing element can also be designed as a pure piston ring or retaining ring.
  • the groove may orbit around the transition element or the flame tube exit to which it is open.
  • the pressure relief recess may extend along the entire side surface of the groove and / or along the entire first side surface of the holding member.
  • pressure relief grooves may extend in the form of segments along the entire side surface of the groove and / or along the entire first side surface of the retaining element. The segmentation causes the holding element or the retaining ring better supported than in the case of an unsegmented circumferential pressure relief well.
  • depressurization depressions may be arranged at different radial positions in the side surface of the groove both within the scope of the component arrangement according to the invention and within the scope of the inventive combustion chamber arrangement.
  • edges of the adjoining side surfaces can be rounded or configured spherical. As a result, the contact surface can be reduced to a minimum.
  • the component assembly according to the invention and the combustion chamber arrangement according to the invention can be used with appropriate choice of materials in principle in any temperature range and with different media, such as air, water or oil.
  • the applied pressures are not limited in principle. If the contact pressure should be too low, in particular the height of the ring in the radial direction can be increased.
  • the gas turbine according to the invention comprises a combustion chamber arrangement according to the invention, as described in the previous paragraphs.
  • the gas turbine according to the invention has the same advantages as the combustion chamber arrangement according to the invention.
  • FIG. 1 schematically shows a gas turbine.
  • a gas turbine has inside a rotor rotatably mounted about a rotation axis with a shaft 107, which is also referred to as a turbine runner.
  • a turbine runner Along the rotor follow each other an intake housing 109, a compressor 101, a plurality of combustor assemblies 15, a turbine 105, and the exhaust case 190.
  • Each combustion chamber arrangement 15 communicates with a, for example, annular hot gas channel.
  • a turbine stage connected in series form the turbine 105.
  • Each turbine stage is formed from two blade rings.
  • the guide vanes 117 are fastened to an inner housing of a stator, whereas the moving blades 115 of a row are attached to the rotor, for example by means of a turbine disk. Coupled to the rotor is a generator or a work machine.
  • FIG. 2 schematically shows a part of a combustion chamber assembly 15 of a gas turbine.
  • combustion chamber assembly 15 may be, for example, a so-called Can combustion chamber.
  • the can combustors are evenly distributed along the circumference and are concentric with the rotor 107.
  • Each combustion chamber assembly 15 comprises a flame tube 8 (combustor basket) and a transition element 11 (transition piece).
  • a flame tube 8 combustor basket
  • transition element 11 transition piece
  • the resulting hot gas is from the flame tube 8 is passed via the transition element 11 to a turbine 105, where it drives the turbine blades 13 located in the turbine 105 as a working medium.
  • the flow direction of the hot gas in the combustion chamber arrangement 15 is indicated by an arrow 14.
  • the center axis of the flame tube 8 and the nested portions of the flame tube 8 and the transition element 11 is indicated by the reference numeral 19.
  • flame tube 8 further comprises an output 9, to which the transition element 11 is connected in such a way that a portion of the outlet 9 of the flame tube 8 is pushed into a portion of the adjoining transition element 11.
  • the nested sections are designed cylindrical. Between the nested portions of the flame tube 8 and the transition element 11, a gap 1 is formed. This gap 1 is previously sealed, for example, by a clamping spring seal 18. In the context of the invention, however, it can preferably be sealed by means of a brush seal or by means of another sealing element which is arranged at least partially in a guide groove.
  • the transition element 11 has a decreasing in the flow direction cross-sectional area, which also converts from a circular area in a ring segment surface.
  • the end of the transition element 11 in the flow direction 14 forms the turbine inlet 12.
  • FIGS. 3 and 4 schematically show a section through two variants of a component assembly according to the invention, which in the present embodiment is a combustion chamber assembly 21 in a gas turbine is.
  • the brush seal 4 comprises a seal holder 6 and a brush 5.
  • the brush 5 is arranged in the seal holder 6 so that the bristles of the brush 5 are partially in the interior of the seal holder 6 and partially protrude from the seal holder 6.
  • the seal holder 6 is designed as a piston ring. This ensures a permanent direct contact of the brush 5 with the surface of the flame tube eighth
  • the portion of the transition element 11 in the FIGS. 3 and 4 has an annular groove 7 extending in the region of the gap 1 to be sealed, with a radial direction, relative to the central axis 20.
  • the seal holder 6 is inserted into this annular groove 7 such that the seal holder 6 is radially displaceable with respect to a central axis 20.
  • the direction of the radial displaceability is indicated by an arrow with the reference numeral 16.
  • the annular groove 7 and the brush holder 6 are further arranged so that the seal holder 6 protrudes partially into the gap 1 and in this way partially seals the gap 1.
  • the part of the gap 1 which is not sealed by the seal holder 6 is sealed by the brush 5 protruding from the seal holder 6 in the direction of the flame tube 8.
  • the bristles of the brush 5 are in direct contact with the surface of the flame tube. 8
  • the radial displaceability of the seal holder 6 in the annular groove 7 allows compensation of possible movements or displacements of the transition element 11 and the flame tube 8 in the radial direction against each other, for example by thermal expansion or mechanical stresses.
  • the seal holder 6 During operation, the seal holder 6 must rest on a side surface 23 of the annular groove 7, since otherwise leakage may occur. The adjoining surfaces must be appropriately clean and plan worked. Typically, the seal holder 6 is pressed against a side surface 23 of the annular groove 7 due to the pressure difference across the seal. In principle, the seal holder 6 in the annular groove 7 should have little freedom of movement in the axial direction.
  • the component assembly shown comprises in the FIG. 3 shown transition element two interconnected, for example, screwed together, components 11a and 11b.
  • the part of the transition element 11 shown can also be made of a component, as shown in the FIG. 4 is shown.
  • the component 11a in the FIG. 3 includes a first side surface 24 and the bottom surface 30 of the groove 7.
  • the component 11b includes a second side surface 23 of the groove 7.
  • the seal holder 6 comprises in the FIGS. 3 and 4 a first side surface 31a and a second side surface 31b.
  • the first side surface 31a of the seal holder 6 of the brush seal 4 can be abutted against the second side surface 23 of the groove 7 by a pressure difference between a pressure applied to the first side surface 31a and a pressure applied to the second side surface 31b.
  • the first side surface 31a of the seal holder 6 of the brush seal 4 on the second side surface 23 of the groove 7 at.
  • the second side surface 23 of the groove 7 has a pressure relief recess 25.
  • the pressure relief recess 25 may have a depth 26 between 1mm and 10mm, preferably 1.5mm.
  • the pressure relief recess 25 may extend in particular along the entire side surface 23 of the groove 7.
  • the pressure relief recess 25 may be configured segmented in the circumferential direction. The segments may in this case extend along the entire side surface 23 of the groove 7. The segmentation causes the seal holder 6 is better supported than in the case of an unsegmented design.
  • an additional seal 33 may be arranged between the adjoining side surfaces 31a and 23. This is particularly advantageous if between the side surface 23 of the groove 7 and the side surface 31a of the seal holder 6 leakage is to be feared.
  • the seal 33 may be, for example, an O-ring or a brush seal.
  • FIG. 4 schematically shows a section through an alternative variant of a component assembly according to the invention. Unlike the one in the FIG. 3 the variant shown on the side surface 23 of the groove 7 first side surface 31a of the seal holder 6, a pressure relief recess 25, which fluidly via a pressure equalization channel 32 connected to area 28, in which the higher pressure prevails.
  • the side surface 23 of the groove 7 in this embodiment does not include a pressure relief recess.
  • the transition element 11 is in the FIG. 4 designed as it is in connection with the FIG. 3 has been described. It can be both two or more parts, as in the FIG. 3 shown, but also one piece, as in the FIG. 4 shown, be designed.
  • depressurization recess 25 has basically the same features and advantages as those in the FIG. 3 It may extend in particular along the entire first side surface 31a of the holding element 6 and be designed segmented, as in connection with the FIG. 3 has been described.
  • the pressure relief recess 25 causes in both in the FIGS. 3 and 4 variants shown a reduction in the pressurized area between the side surface 23 of the groove 7 and the first side surface 31a of the seal holder 6 and thus a reduction in the friction between them.
  • the reduction of the pressurized area also reduces the acting thrust.
  • the combustion chamber arrangement according to the invention can also be designed so that the proportion of the flame tube 8, which with the Transition member 11 is arranged overlapping, so the output 9 of the flame tube 8, the groove 7 includes.
  • the remarks made above also apply accordingly for this variant.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Sealing Devices (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP08009563A 2008-05-26 2008-05-26 Bauteilanordnung, Brennkammeranordnung und Gasturbine Ceased EP2128524A1 (de)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP08009563A EP2128524A1 (de) 2008-05-26 2008-05-26 Bauteilanordnung, Brennkammeranordnung und Gasturbine
JP2009125611A JP5543132B2 (ja) 2008-05-26 2009-05-25 部品配置構造、燃焼器装置およびガスタービン
US12/471,534 US20090288422A1 (en) 2008-05-26 2009-05-26 Component arrangement, combustion chamber arrangement and gas turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08009563A EP2128524A1 (de) 2008-05-26 2008-05-26 Bauteilanordnung, Brennkammeranordnung und Gasturbine

Publications (1)

Publication Number Publication Date
EP2128524A1 true EP2128524A1 (de) 2009-12-02

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP08009563A Ceased EP2128524A1 (de) 2008-05-26 2008-05-26 Bauteilanordnung, Brennkammeranordnung und Gasturbine

Country Status (3)

Country Link
US (1) US20090288422A1 (ja)
EP (1) EP2128524A1 (ja)
JP (1) JP5543132B2 (ja)

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DE102011108273A1 (de) * 2011-07-21 2013-01-24 Howaldtswerke-Deutsche Werft Gmbh Dichtungsanordung
WO2014143325A1 (en) * 2013-03-15 2014-09-18 Copeland Andrew D Seal assembly for a gas turbine engine and method of forming a turbine engine component
EP2806216A1 (en) * 2013-05-21 2014-11-26 Mitsubishi Hitachi Power Systems, Ltd. Regenerative gas turbine combustor
DE102008061870B4 (de) * 2008-12-15 2015-10-22 Carl Freudenberg Kg Dichtring, Dichtungsanordnung mit einem Dichtring und Verwendung einer Dichtungsanordnung und eines Dichtrings
EP3306199A1 (en) * 2016-10-06 2018-04-11 Ansaldo Energia Switzerland AG Combustor device for a gas turbine engine and gas turbine engine incorporating said combustor device
US10533750B2 (en) 2014-09-05 2020-01-14 Siemens Aktiengesellschaft Cross ignition flame duct

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US8707673B1 (en) * 2013-01-04 2014-04-29 General Electric Company Articulated transition duct in turbomachine
WO2014179328A1 (en) * 2013-04-29 2014-11-06 United Technologies Corporation Joint for sealing a gap between casing segments of an industrial gas turbine engine combustor
US9759427B2 (en) * 2013-11-01 2017-09-12 General Electric Company Interface assembly for a combustor
CN104196637A (zh) * 2014-08-15 2014-12-10 江苏透平密封高科技有限公司 一种新型燃气轮机尾筒气封及其制造方法
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KR101850922B1 (ko) * 2016-10-07 2018-04-20 두산중공업 주식회사 가스터빈용 연소 덕트 조립체
US20180306120A1 (en) 2017-04-21 2018-10-25 General Electric Company Pressure regulated piston seal for a gas turbine combustor liner
GB201814673D0 (en) * 2018-09-10 2018-10-24 Rolls Royce Plc Radially displaceable brush seal
GB201814674D0 (en) * 2018-09-10 2018-10-24 Rolls Royce Plc Radially dispaceable brush seal
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Publication number Priority date Publication date Assignee Title
DE102008061870B4 (de) * 2008-12-15 2015-10-22 Carl Freudenberg Kg Dichtring, Dichtungsanordnung mit einem Dichtring und Verwendung einer Dichtungsanordnung und eines Dichtrings
DE102011108273A1 (de) * 2011-07-21 2013-01-24 Howaldtswerke-Deutsche Werft Gmbh Dichtungsanordung
WO2014143325A1 (en) * 2013-03-15 2014-09-18 Copeland Andrew D Seal assembly for a gas turbine engine and method of forming a turbine engine component
US9051882B2 (en) 2013-03-15 2015-06-09 Rolls-Royce Corporation Seals for a gas turbine engine
EP2806216A1 (en) * 2013-05-21 2014-11-26 Mitsubishi Hitachi Power Systems, Ltd. Regenerative gas turbine combustor
US10151241B2 (en) 2013-05-21 2018-12-11 Mitsubishi Hitachi Power Systems, Ltd. Sealing mechanism for a regenerative gas turbine combustor
US10533750B2 (en) 2014-09-05 2020-01-14 Siemens Aktiengesellschaft Cross ignition flame duct
EP3306199A1 (en) * 2016-10-06 2018-04-11 Ansaldo Energia Switzerland AG Combustor device for a gas turbine engine and gas turbine engine incorporating said combustor device
US10851997B2 (en) 2016-10-06 2020-12-01 Ansaldo Energia Switzerlang Ag Combustor device for a gas turbine engine and gas turbine engine incorporating said combustor device

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US20090288422A1 (en) 2009-11-26
JP2009287559A (ja) 2009-12-10

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