EP2201299B1 - Stützring für hitzeschildelemente eines flammenrohrs und eine brennkammeranordnung mit einem derartigen stützring - Google Patents

Stützring für hitzeschildelemente eines flammenrohrs und eine brennkammeranordnung mit einem derartigen stützring Download PDF

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Publication number
EP2201299B1
EP2201299B1 EP08842468A EP08842468A EP2201299B1 EP 2201299 B1 EP2201299 B1 EP 2201299B1 EP 08842468 A EP08842468 A EP 08842468A EP 08842468 A EP08842468 A EP 08842468A EP 2201299 B1 EP2201299 B1 EP 2201299B1
Authority
EP
European Patent Office
Prior art keywords
support ring
flame tube
groove
combustion chamber
groove wall
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP08842468A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2201299A2 (de
Inventor
Elke Henschel
Milan Schmahl
Martin Stapper
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 PL08842468T priority Critical patent/PL2201299T3/pl
Publication of EP2201299A2 publication Critical patent/EP2201299A2/de
Application granted granted Critical
Publication of EP2201299B1 publication Critical patent/EP2201299B1/de
Active 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
    • F23R3/007—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
    • F23R3/60—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
    • 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
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes

Definitions

  • the present invention relates to a support ring for heat shield elements of a flame tube, in particular a flame tube of a gas turbine.
  • the invention relates to a combustion chamber arrangement with a flame tube and a mixing housing, as it finds particular use in gas turbines.
  • Support rings for heat shield elements may have a groove extending on its outer side, which serves as a cooling air passage.
  • a section of a support ring according to the prior art is in FIG. 1 illustrated, wherein the support ring is received by the batt ring of a mixing housing.
  • the figure shows a section of the support ring 1 and a section of a peg 3 of a mixing housing in a schematic cross-sectional view.
  • the support ring has a reinforced portion 5, which in turn is provided with an inner groove 7 and an outer groove 9, both of which extend over the full circumference of the support ring.
  • the outer groove 9 and the inner groove 7 are fluidly connected to each other via a number of radial through holes 11.
  • the outer groove 9 forms a fresh air supply for cooling the support ring 1.
  • the fresh air is then passed through the holes 11 into the combustion chamber interior.
  • the reinforced area 5 also forms a flange-like projection projecting toward the interior of the combustion chamber, which forms a support for heat shield elements.
  • the object of the present invention is to provide an advantageous support ring and an advantageous combustion chamber arrangement, which in particular make it possible to extend the maintenance intervals for the transition between the flame tube and the mixing housing.
  • a flame tube in particular a gas turbine flame tube
  • at least one groove is present. This has a relation to the radial direction of the support ring obliquely extending groove wall. Suitable angles between the surface normal of the oblique groove wall to the radial direction of the support ring are in particular in the range between 30 ° and 60 °.
  • the oblique groove wall leads when grinding the Zinnenkranzes a mixing housing in the support ring that forms a wedge-shaped projection in the pinnacles. This has one of the oblique groove wall corresponding wedge surface. If, when switching off the gas turbine due to the different thermal expansion behavior of mixing housing and support ring in the axial direction of the support ring acting forces occur, the slope leads to acting in the radial direction of the support ring forces are generated which separate the pinnacles from the support ring. As a result, in particular the tearing off of pinnacles due to an excessive force in the axial direction of the support ring is avoided.
  • passage openings may be located in the region of the groove which extend from the outside of the support ring to its inner side and serve as cooling air openings for cooling the support ring and for removing cooling air introduced through the groove.
  • the groove wall opposite the oblique groove wall may have a non-planar geometry. In particular, it may form a curved surface in the axial direction of the support ring.
  • a wear-resistant layer hard-facing, wear-resistant layer
  • a combustion chamber arrangement according to the invention has a flame tube and a mixing housing. It can be used in particular in gas turbines.
  • the flame tube has an output end with a support ring for heat shield elements, in particular for ceramic heat shield elements.
  • the mixing housing has an edge with protruding pinnacles, wherein the pinnacles form a receiving portion for receiving the support ring.
  • the Support ring designed as a support ring according to the invention.
  • the armor of the pinnacles can be harder than the armor of the support ring.
  • the armor can also be the same, or the armor of the support ring may be harder than the armor of the battlements.
  • the armor of the merlons is harder than that of the support ring, since a mending and replacing the support ring in comparison to a repair or replacement of battlements represents less effort.
  • a demolition of battlements with the same armor is more likely than damage to the support ring and has more critical consequences for the gas turbine.
  • a combustion chamber arrangement according to the invention which has a support ring according to the invention for heat shield elements, also called a stone support ring, will be described below with reference to FIGS FIGS. 3 to 7 described.
  • the present embodiment shows a combustion chamber arrangement in which the flame tube is arranged vertically, ie, the axial direction of the flame tube extends in the vertical direction.
  • the radial directions of the flame tube represent horizontal directions. The hot gas flowing out of the flame tube in the vertical direction is deflected by the mixing housing in a horizontal flow direction.
  • FIG. 3 shows the combustion chamber assembly, which has a flame tube 101 with a burner end 103, on which the burner (not shown) are arranged, and an outlet end 105, from which occur in the combustion chamber resulting hot gases occur, in a sectional view.
  • the flame tube 101 is inserted with its outlet end 105 into a receptacle 109 of a mixing housing 107.
  • the mixing housing passes the hot gases leaving the flame tube 101 to the turbine (not shown).
  • the interior of the flame tube 101 is provided with ceramic heat shield elements, also called heat shield stones, to protect the combustion chamber wall from the corrosive hot gas.
  • the heat shield stones 111 holding stone support ring 113 is arranged, of which a substantial part in the receptacle 109 of the mixing housing 107 is located.
  • the receiving portion 109 and the stone support ring 113 are in FIG. 4 partially enlarged.
  • the stone support ring 113 has an outer side 115 and an inner side 117. Both in the outside 115, and in the inside 117 grooves 119, 121 are present, which extend over the entire circumference of the stone support ring 113.
  • the outside of the stone support ring 113 is also provided with an abrasion-reducing armor 129.
  • At regular intervals distributed around the circumference of the stone support ring 113 through holes 123 are present, which connect the groove 119 in the outer side 117 (hereinafter called outer groove 119) with the formed in the inner side 117 groove 121 (hereinafter referred to as inner groove 121) fluidly connect.
  • the outer groove 119 serves as a cooling air passage, which allows the distribution of cooling air around the stone support ring 113 around.
  • the cooling air can then pass from the outer groove 119 through the through holes 123 in the inner groove 121 and from there into the combustion chamber interior.
  • the outer groove 117 and the inner groove 121 are disposed in a flange-like protrusion 122 protruding radially toward the combustion chamber interior.
  • the upper surface 124 of the projection 122 forms a support surface for the lowermost row of the heat shield elements 111 (see FIG FIG. 3 ).
  • the outer groove 119 of the stone support ring 113 has an inclined with respect to the radial direction of the stone support ring 113 groove wall 125.
  • the surface normal of the oblique groove wall 125 includes with the radial direction of the support ring 113 an angle between 30 ° and 60 °. In the present embodiment, the angle is about 40 °.
  • the oblique groove wall 125 opposite groove wall 127 has a non-planar geometry and is curved in the present embodiment in the axial direction of the support ring 113.
  • a section through the stone support ring 113 along the line VV in FIG. 4 is in FIG. 5 shown. It can be seen in this that the through holes 123 do not extend in the radial direction of the support ring 113, but are inclined in the circumferential direction and enclose an angle of about 60 ° with the radial direction.
  • the stone support ring 113 of the flame tube 101 is inserted into the receiving portion 109 of the mixing housing 107.
  • This receiving portion 109 is formed by pinnacles 133, which are formed in the wall 131 of the mixing housing.
  • the pinnacles 133 are in this case formed by a wall section of the mixing housing, which is penetrated by circumferentially distributed around the mixing housing recesses or recesses. These recesses or recesses extend from the edge of the peripheral wall, starting substantially in the axial direction of the flange into the peripheral wall.
  • the receiving section 109 is given an increased flexibility with respect to the wall section of the mixing housing 107 which is not provided with the recesses or recesses, so that forces occurring between the mixing housing 107 and the flame tube 101 can be compensated to a certain extent.
  • the inner sides 135 of the pinnacles 133 are planar and provided with an armor 137.
  • the armor 137 of the merlons is harder than the armor 129 of the outside 115 of the stone support ring 113, so that occurring during operation abrasion caused by friction of the stone support ring 113 on the inside of the pinnacles 133, to a large extent on the stone support ring 113 concentrated.
  • FIG. 6 shows a section of the stone support ring 113 and the receiving portion 109 when the combustion chamber assembly has reached a certain operating time.
  • the Zinnenkranz of the mixing housing 107 grinds into the stone support ring 113 of the flame tube 101, if no previous findings and replacement or repair takes place. This condition is in FIG. 6 shown.
  • the grinding creates a projection 139 in the pinnacles 133, which protrudes into the outer groove 119, that is, into the cooling air passage.
  • this projection 139 has an oblique side 141 which is largely parallel to the oblique groove wall 125.
  • the oblique groove wall 125 and the oblique side 141 created during grinding in the projections 139 of the pinnacles thus lead to a bevelled contact surface in relation to the radial direction and the axial direction of the two components, which uses or generates the forces generated by transient movement of the components with temperature changes ., converts the components independently of each other, ie, they are pushed apart, and the forces that occur do not cause any consequential damage, such as tearing of battlements, deformation, etc.
  • a force diagram which transiently the force F caused by transient motion and the force exerted on the flame tube resultant force F and the resulting result.Fl the mixing housing force F result.Mi shows, in FIG. 7 shown.
  • the curved side 127 of the outer groove 119 in the stone support ring 113 also causes even with considerable wear and an associated deep digging of the pinnacles 133 in the outer groove 119 of the stone support ring 113 always given a sufficiently large cooling air passage for the stone support ring is. An obstruction of thedeluftpasssage can be avoided.
  • the groove wall 127 opposite the inclined groove wall 125 is curved
  • the groove wall can be roof-shaped, that is to say with two planar wall sections which meet one another at an angle. In the simplest case, this can be realized by a rectangular in cross-section groove is introduced at an angle relative to the radial direction of the stone support ring 113 in the outside 115.
  • the angle which the groove encloses with the radial direction is in this case preferably in the range between 30 ° and 60 °. In order to avoid blockage of the cooling air passage by a deeper incorporation of the battlements (abandoned by a longer operation), they can be introduced beyond the height of the possible incorporated batt in the support ring.
  • the stone support ring is provided in the region of the groove (cooling air supply) with a slope (for example 40 °, but the slope is variable and functionally selected), which has a forced demolition of mixing housing and stone support ring result in cooling of the components.
  • a slope for example 40 °, but the slope is variable and functionally selected

Landscapes

  • 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)
  • Combustion Of Fluid Fuel (AREA)
  • Portable Nailing Machines And Staplers (AREA)
  • Gas Burners (AREA)
EP08842468A 2007-10-26 2008-10-23 Stützring für hitzeschildelemente eines flammenrohrs und eine brennkammeranordnung mit einem derartigen stützring Active EP2201299B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL08842468T PL2201299T3 (pl) 2007-10-26 2008-10-23 Pierścień podporowy dla elementów osłony cieplnej płomienicy i układ komory spalania z tego rodzaju pierścieniem podporowym

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102007051649 2007-10-26
PCT/EP2008/064333 WO2009053417A2 (de) 2007-10-26 2008-10-23 Stützring für hitzeschildelemente eines flammenrohrs und eine brennkammeranordnung mit einem derartigen stützring

Publications (2)

Publication Number Publication Date
EP2201299A2 EP2201299A2 (de) 2010-06-30
EP2201299B1 true EP2201299B1 (de) 2011-05-11

Family

ID=40340467

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08842468A Active EP2201299B1 (de) 2007-10-26 2008-10-23 Stützring für hitzeschildelemente eines flammenrohrs und eine brennkammeranordnung mit einem derartigen stützring

Country Status (6)

Country Link
EP (1) EP2201299B1 (ru)
CN (1) CN101855497B (ru)
AT (1) ATE509236T1 (ru)
PL (1) PL2201299T3 (ru)
RU (1) RU2478881C2 (ru)
WO (1) WO2009053417A2 (ru)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012204103A1 (de) * 2012-03-15 2013-09-19 Siemens Aktiengesellschaft Hitzeschildelement für einen Verdichterluftbypass um die Brennkammer
DE102017207392A1 (de) 2017-05-03 2018-11-08 Siemens Aktiengesellschaft Silobrennkammer und Verfahren zum Umrüsten einer solchen

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE8618859U1 (de) * 1986-07-14 1988-01-28 Siemens AG, 1000 Berlin und 8000 München Hitzeschild
EP0539359B1 (de) * 1990-07-17 1994-04-20 Siemens Aktiengesellschaft Rohrstück, insbesondere Flammrohr, mit gekühltem Stützrahmen für eine hitzefeste Auskleidung
US5749218A (en) * 1993-12-17 1998-05-12 General Electric Co. Wear reduction kit for gas turbine combustors
GB2298267B (en) * 1995-02-23 1999-01-13 Rolls Royce Plc An arrangement of heat resistant tiles for a gas turbine engine combustor
RU2212591C1 (ru) * 2002-05-16 2003-09-20 Открытое акционерное общество "Научно-производственное объединение "Сатурн" Кольцевая камера сгорания газотурбинного двигателя
RU2300706C2 (ru) * 2005-05-05 2007-06-10 Открытое акционерное общество "Авиадвигатель" Трубчато-кольцевая камера сгорания газотурбинного двигателя
EP2049840B1 (de) * 2006-08-07 2018-04-11 Ansaldo Energia IP UK Limited Brennkammer einer verbrennungsanlage

Also Published As

Publication number Publication date
ATE509236T1 (de) 2011-05-15
EP2201299A2 (de) 2010-06-30
CN101855497A (zh) 2010-10-06
PL2201299T3 (pl) 2011-10-31
RU2010121163A (ru) 2011-12-10
WO2009053417A2 (de) 2009-04-30
RU2478881C2 (ru) 2013-04-10
CN101855497B (zh) 2012-09-05
WO2009053417A3 (de) 2010-05-20

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