WO2017032424A1 - Élément d'écran thermique métallique à circulation d'air de refroidissement optimisée - Google Patents

Élément d'écran thermique métallique à circulation d'air de refroidissement optimisée Download PDF

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Publication number
WO2017032424A1
WO2017032424A1 PCT/EP2015/069661 EP2015069661W WO2017032424A1 WO 2017032424 A1 WO2017032424 A1 WO 2017032424A1 EP 2015069661 W EP2015069661 W EP 2015069661W WO 2017032424 A1 WO2017032424 A1 WO 2017032424A1
Authority
WO
WIPO (PCT)
Prior art keywords
cooling air
heat shield
shield element
edge
cold side
Prior art date
Application number
PCT/EP2015/069661
Other languages
German (de)
English (en)
Inventor
Andreas Böttcher
Tobias Krieger
Kai-Uwe Schildmacher
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to PCT/EP2015/069661 priority Critical patent/WO2017032424A1/fr
Priority to CN201580082712.5A priority patent/CN107923616B/zh
Priority to EP15756635.7A priority patent/EP3320266B1/fr
Publication of WO2017032424A1 publication Critical patent/WO2017032424A1/fr

Links

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
    • F23R3/002—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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03043—Convection cooled combustion chamber walls with means for guiding the cooling air flow
    • 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 heat shield element for use in a heat shield, in particular for lining a combustion chamber wall of a gas turbine.
  • a heat shield is used in a known manner, which causes a separation between the hot combustion chamber and the structure to be protected from thermal damage behind the heat shield.
  • the heat shield tiles or the heat shield elements generally have a planar or slightly curved shape with a pointing to the combustion chamber hot side and an opposite cold side and peripheral edges. These are each fastened to a support structure arranged below the heat shield tiles or heat shield elements. In a multiple arrangement next to each other a largely closed heat shield is formed.
  • the heat shield tiles or the heat shield elements are spaced positioned to each other so as to form in each case a lateral gap between the edges of adjacent heat shield elements.
  • the sides tenspalt between the heat shield tiles or heat shield elements is required to be able to accommodate different thermal expansions between ⁇ from the heat shield tiles or the heat shield elements and the supporting structure arranged thereunder.
  • heat shield tiles or heat shield elements are usually inadequate to prevent progressive damage. Therefore, in known manner cooling air used to prevent the emergence of critical ⁇ shear component temperatures.
  • the heat shield tiles and heat shield elements have a higher Temperaturbe ⁇ resistance
  • metallic heat shield elements are, in particular to cool during operation of the gas turbine.
  • Particular risk of damage to components by overheating by a so-called H disclosegaseinzug starting from the combustion chamber is in the fasteners for fixing the heat shield tiles or heat shield elements and on the supporting structure of the heat shield in the side column zwi ⁇ tween the heat shield tiles or heat shield elements and at the end the heat shield in the transition to the subsequent
  • Cooling air is applied.
  • the cooling air into the side column have two opposing edge portions on a plurality of spaced in a row of cooling air holes ⁇ . Through this, the cooling air is directly in the Side gap injected and thus an intrusion of
  • Object of the present invention is therefore to improve the distribution of cooling air over the length of the gap, taking into account the ⁇ arrangement of the heat shield elements in several rows.
  • the generic heat shield element forms a part of a heat shield ⁇ part, this is in particular provided for Ver ⁇ use in a combustion chamber of a gas turbine.
  • a plurality of generic heat shield elements are used on the heat shield.
  • the heat shield element initially comprises a wall. This wall has ei ⁇ ne acted upon by a hot medium hot side and one of the hot side opposite cold side.
  • Be ⁇ part of the heat shield in its use in the combustion chamber has insofar the hot side of the Hitzeschildele ⁇ ment to the hot gas having interior of the combustion chamber, while the cold side is oriented pointing away from the combustion chamber.
  • the wall can in this case be staltung executed planar, but also have a single or multiple curved shape.
  • At least the heat shield element has a peripheral edge surrounding the wall. At least two opposing first edge portions are arranged on this.
  • the first edge portions are substantially parallel to each other along a longitudinal direction. Provided that it is a planar wall with rectangular shape delt Han, so the first edge portions are parallel zuei ⁇ Nander rectilinearly in the longitudinal direction.
  • the first edge sections extend approximately parallel to one another and in this case essentially in the longitudinal direction.
  • At least the first edge portions are to be performed such that side by side in each case, a substantially uniform gap between the adjacent first edge portions results in a voltage of three Anord ⁇ same generic heat shield elements.
  • the first edge portions of the heat shield element in this case extend from the hot side to the cold over ⁇ side, up to a ridge top.
  • a plurality of cooling air openings are distributed in the first edge portions distributed over the length of the edge portion, which extend from an inner side of the respective edge portion to an outer side of the respective Randab ⁇ section .
  • At least one cooling air pocket is now introduced for further optimization of the cooling air distribution in the gap in the wall.
  • This cooling air pocket is arranged here on the cold side and thus dips, starting from the cold side in the wall in the direction of the hot side.
  • This cooling air pocket is in the range of a first cooling air To arrange opening. It is necessary that the cooling air bag from the inside, starting in a cross ⁇ direction, that is substantially transverse to the inner side, extends. To achieve the required improvement of the cooling air distribution, it is necessary that the first cooling air ⁇ opening is arranged at least partly within thede Kunststoffta ⁇ cal. Thus, turned on the cold side ⁇ directed cooling air, the cooling air pocket are crossing into the first cooling air opening.
  • the cooling air pocket is achieved if this has an advantageous size in relation to the first cooling air opening. Therefore, the admiss ⁇ te free cross section of the cooling air opening cut asde Kunststoffquer- is used comparatively.
  • the cooling air pocket at least partially in its Ver ⁇ run from the inside of the first edge portion to En ⁇ de the cooling air pocket, a first cross-sectional area of ⁇ at least 0, 5-fold and at most 10 times the cooling air cross-section on. Hierei becomes a first
  • Cross-sectional area considered parallel to the selected cooling air cross-section it is particularly advantageous if the first cross-sectional area of the cooling air pocket corresponds at least to the simple and at most 5 times the cooling air cross-section.
  • This advantageous shape of thede Kunststoffta ⁇ cal is on the one hand ensures that effectively sufficient cooling air of the first cooling air opening can be supplied through the cooling air pocket. On the other hand, it avoids that the cooling air pocket reaches an unnecessary size, which is no longer effective for improving the cooling air distribution.
  • the selected second cross-sectional area lies in a plane which runs essentially centrally through the cooling air opening and is aligned essentially transversely to the cooling air cross-section.
  • Particularly advantageous in this case is a choice of at least 2 times and at most 10 times the cooling air cross section for the second cross-sectional area of the cooling air pocket.
  • the size of the cooling air pocket taking into account the dimension of the heat shield element.
  • thede povertyta ⁇ specific an extension in the transverse direction transversely to the inner side of the first edge portion of at least the 0.05 times and maxi ⁇ times 0.2 times the width of the heat shield element, gemes ⁇ sen in the same direction as the extension of the Cooling air pocket has.
  • the design of the cooling air pocket within these size ratios has to be advantageous with regard lent the supply of cooling air from the cold side into the cooling air bag for passage through the first cooling air opening ⁇ proven.
  • a rea ⁇ chender cross-section for realizing the cooling air bag to direct the cooling air flow through the first cooling air opening is provided on the one hand, as well as the wall is weakened unnecessarily by the A ⁇ bring the cooling air bag.
  • the concrete embodiment of the cooling air pocket is initially irrelevant, provided that sufficient flow is ensured by the cold air side through the cooling air pocket in the first cooling air opening. For this purpose, however, it is advantageous if the peripheral edges of the cooling air pocket are flattened out ⁇ leads, or are rounded in the transition to the cold side.
  • the first cool-air opening is arranged in sections of the attached ⁇ cooling air bag in the area.
  • Particularly advantageous is an arrangement of the first cooling air opening when it is angeord ⁇ net on the inside with at least 40% but not more than 60% within the cooling air pocket. This leads quasi to the arrangement of the first cooling air opening centrally to the cold side, so that approximately half of the first cooling air opening above the cold side and the other half of the first cooling air opening below the Kaltsei ⁇ te are arranged.
  • the design of the cooling air pocket in conjunction with the first cooling air opening leads to an advantageously flush arrangement of the first cooling air opening to the bottom of the cooling air pocket. Deviating from this, however, it is without disadvantage if a small distance from the bottom of the cooling air pocket to the first cooling air opening is present. This is advantageously at most 0.5 times the depth of thede Kunststoffta- see, i. the distance from the cold side to the bottom of the
  • Cooling air pocket Particularly advantageously, the distance from the bottom to the first cooling air opening is at most 0.25 times the depth of the cooling air pocket.
  • the cooling air openings extending substantially oriented from the inside of the first edge portion to the outside of the first edge portion perpendicular ⁇ right to the inside or to the outside. Irrelevant are related angular deviations of +/- 15 degrees.
  • the material thickness of the first edge portions is at least 0.5 times the Mate ⁇ rialpark the wall and a maximum of 2 times the material strength of the wall. This leads to an advantageous ⁇ liable strength and avoids unnecessary thermal stresses. Be ⁇ Sonders advantageous if the material thickness of ers ⁇ th edge portions substantially corresponds to the material thickness of the wall is.
  • the second edge distance extends well cut from the hot side to the cold side over ⁇ .
  • the Hitzeschildele ⁇ ment comprises a arranged on the cold side rib. This also applies between the two first edge sections to be connected in a raised manner on the cold side, the latter extending at a distance substantially parallel to the second edge section.
  • the first cooling air opening with the cooling air ⁇ bag is thereby located between the rib and the two ⁇ th edge portion.
  • the further cooling air openings are arranged on the opposite side of the rib, ie on the side of the rib which is turned away from the second edge section.
  • the concrete embodiment of the second edge portion so ⁇ as the concrete embodiment of the rib is uner ⁇ considerably initially, which are carried out in a particularly advantageous manner in We ⁇ sentlichen coincident with the first edge portions and in so far as extend to the web upper side of the first edge portions. These have a substantially matching material thickness with the first edge portions and are also aligned substantially perpendicular to the hot side or substantially perpendicular to the cold side, with an angular deviation of +/- 15 degrees is also considered negligible.
  • the heat shield element according to the invention leads to a novel heat shield according to the invention using a heat shield element according to the invention.
  • the heat shield is provided in particular for use in a combustion chamber of a gas turbine.
  • the heat shield at least partially forms the wall of the combustion chamber.
  • the heat shield tiles or the heat shield elements are in this case sur fa ⁇ chig under load adjacent to one another in each case a gap.
  • a fully encircling series of heat shield elements is each provided ⁇ wells with a heat shield element according to the above exemplary form in the heat shield and so far at least comprise each a cooling ⁇ air bag at a first cooling air opening.
  • an arrangement of heat shield elements according to the invention in a circumferential row is such necessary that the first edge portions of the respective heat shield elements arranged adjacent to each other at the gap, wherein the second Randab ⁇ sections are positioned in extension of each other.
  • the circumferential row of inventive heat shield elements are arranged in the particularly advantageous heat shield at the downstream end of the heat shield.
  • the individual ⁇ a heat shield elements are such aligned such that the two edge portions of the heat shield element for downstream ge ⁇ superior end of the heat shield have.
  • FIG. 1 shows schematically a combustion chamber of a gas turbine with a heat shield
  • Figure 2 is an exemplary embodiment of a fiction, modern ⁇ heat shield element in a perspective view on the cold side.
  • FIG. 3 is a detail view of a corner region of the heat ⁇ shield member of FIG .. 2
  • FIG. 1 shows schematically and by way of example a section through the combustion system of a combustion chamber 26.
  • Burners 27 are arranged in the upper region of the combustion chamber 26 in inlet openings. There the mixing of the fuel with the compressor air takes place. In the combustion chamber 26, the combustion takes place. Through the outlet at the downstream end 24 of the combustor 26, the hot combustion gases pass into a turbine where they strike the first stationary vane 28.
  • the combustion chamber 26 is lined with ceramic heat shield tiles 23 and metallic heat shield elements 01, which are fastened to the support structure 22 of the heat shield 21.
  • FIG. 2 shows schematically and exemplary a metalli ⁇ ULTRASONIC heat shield element 01 in embodiment according to the invention for use in a heat shield 21 for a combustor 26 of a gas turbine.
  • the heat shield element 01 comprises a wall 03, the 03 one with a hot medium
  • the wall has a curved shape and is designed substantially rectangular.
  • two opposite ERS te edge portions 06 are provided which 06 to 04 extend from the hot side to ⁇ on the cold side 05, up to a ridge top ⁇ 07th
  • the first edge portions 06 duri ⁇ fen case in a longitudinal direction of the heat shield member 01.
  • the longitudinal direction corresponds in this exemplary embodiment play in the exemplary application in which in Fig. 1 illustrated heat shield approximately to the direction of flow.
  • the two opposite first edge portions 06 each have an inner surface 08 extending from the cold side 05 to the web upper side 07 and an outer side 09 extending from the hot side 04 to the web upper side.
  • a second edge portion 16 which 16 connects at the corners 18 of the heat shield ⁇ elements 01, the two ends of the opposite first edge portions 06 together.
  • This 16 is essentially identical to the first edge sections 06 and extends transversely to these 06.
  • This embodiment further comprises a parallel and spaced from the second edge portion 16 extending rib 17, which 17 arranged on the cold side 05 also connects the two first edge portions 06 together.
  • a plurality of cooling air openings 11, 12 are present, wherein a first cooling air opening 12 is arranged as the first in the row of the plurality of cooling air openings 11, 12 between the second edge portion 16 and the rib 17, while all other cooling air ⁇ openings 11 are arranged on the side facing away from the second edge portion 16 side of the rib 17.
  • a cooling air pocket 13 is present in the wall 03 starting from the cold side 04.
  • 3 shows in a detailed view in the region of the corner 18 of the heat shield element Ol of FIG. 2 with the first cooling air opening 12 and the cooling air pocket 13. This 13 extends from the inside 08 across the inside 08, ie substantially corresponding to the alignment of the first cooling air opening 12.
  • the first cooling air opening 12 is arranged at approximately the half of the cooling air within pocket 13, ie the center of the first cooling air ⁇ opening 12 is located approximately at the level of the cold side 04th
  • the dimension of the cooling air pocket 13 are chosen such that a sufficient flow of cooling air into the firstdeluftöff ⁇ tion 12 is made possible, but no unnecessary weakening of the wall 03 takes place. Therefore, in this embodiment, the cooling air pocket 13 was designed with a depth which is ge ⁇ slightly lower than it requires the first cooling air opening 12. Furthermore, the cross section of the cooling air pocket 13 in a plane parallel to the inside 08 - thede Kunststoffboh ⁇ ments 11, 12 are aligned substantially transverse to the inside 08 and 08 outside - about twice as large as a smallest cooling air cross-section of the first cooling air hole 12, wherein the Cross-section increasingly decreases towards the end ofde povertyta ⁇ cal 13. The length of the cooling air pocket 13 transversely to the inside, ie in the direction of the first cooling air opening 12, is approximately 2.5 times the material thickness of the first edge portion 06 in the region of the first cooling air ⁇ opening 12th
  • the heat shield elements are disposed 01 at the downstream end 24 of the heat shield 21, wherein each of the first edge portions 06 Benach via a gap ⁇ are disclosed aligned.
  • the second edge sections 16 with the first cooling air openings 12 located at the corners 18 with the cooling air pockets 13 are also arranged downstream, for example. That is, the Hitzeschildele ⁇ elements 01 are aligned with the second edge portions 16 to the Leitschau ⁇ feln 28-setting.

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

Abstract

L'invention concerne un élément d'écran thermique (01) pour un écran thermique (21) destiné à une chambre de combustion (26) d'une turbine à gaz. Cet élément d'écran thermique comprend une paroi (03) présentant un côté chaud (04), et un côté froid (05) situé à l'opposé du côté chaud (04), et deux premières parties bors (06) opposées, qui s'étendent chacune depuis le côté chaud (04) jusqu'au-delà du côté froid (05), et dans lesquelles sont ménagées plusieurs entrées d'air de refroidissement (11, 12) réparties sur la longueur desdites parties bords. Afin d'améliorer la ventilation de l'interstice latéral entre deux éléments d'écran thermique (01), au moins une cavité à air de refroidissement (13) s'étendant depuis le côté froid est formée dans la paroi (03). Cette cavité à air de refroidissement est agencée dans la région d'une première entrée d'air de refroidissement (11, 12).
PCT/EP2015/069661 2015-08-27 2015-08-27 Élément d'écran thermique métallique à circulation d'air de refroidissement optimisée WO2017032424A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
PCT/EP2015/069661 WO2017032424A1 (fr) 2015-08-27 2015-08-27 Élément d'écran thermique métallique à circulation d'air de refroidissement optimisée
CN201580082712.5A CN107923616B (zh) 2015-08-27 2015-08-27 冷却空气优化的金属隔热元件
EP15756635.7A EP3320266B1 (fr) 2015-08-27 2015-08-27 Élément d'écran thermique métallique à circulation d'air de refroidissement optimisée

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/EP2015/069661 WO2017032424A1 (fr) 2015-08-27 2015-08-27 Élément d'écran thermique métallique à circulation d'air de refroidissement optimisée

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WO2017032424A1 true WO2017032424A1 (fr) 2017-03-02

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EP (1) EP3320266B1 (fr)
CN (1) CN107923616B (fr)
WO (1) WO2017032424A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2019015925A1 (fr) * 2017-07-21 2019-01-24 Siemens Aktiengesellschaft Procédé pour augmenter la puissance d'une turbine à gaz

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113933061B (zh) * 2021-09-30 2024-04-19 中国联合重型燃气轮机技术有限公司 静叶模拟器和具有其的燃烧室试验装置

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013135702A2 (fr) * 2012-03-15 2013-09-19 Siemens Aktiengesellschaft Élément écran thermique pour une dérivation d'air de compresseur autour de la chambre de combustion
WO2013135859A2 (fr) * 2012-03-16 2013-09-19 Siemens Aktiengesellschaft Dérivation de chambre de combustion annulaire

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090235668A1 (en) * 2008-03-18 2009-09-24 General Electric Company Insulator bushing for combustion liner
CN103968418B (zh) * 2014-05-26 2015-12-30 西北工业大学 一种用于加力燃烧室的双层壁隔热屏

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013135702A2 (fr) * 2012-03-15 2013-09-19 Siemens Aktiengesellschaft Élément écran thermique pour une dérivation d'air de compresseur autour de la chambre de combustion
WO2013135859A2 (fr) * 2012-03-16 2013-09-19 Siemens Aktiengesellschaft Dérivation de chambre de combustion annulaire

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2019015925A1 (fr) * 2017-07-21 2019-01-24 Siemens Aktiengesellschaft Procédé pour augmenter la puissance d'une turbine à gaz
CN110945211A (zh) * 2017-07-21 2020-03-31 西门子股份公司 用于提高燃气轮机的性能的方法

Also Published As

Publication number Publication date
CN107923616B (zh) 2019-12-13
EP3320266B1 (fr) 2019-03-20
CN107923616A (zh) 2018-04-17
EP3320266A1 (fr) 2018-05-16

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