EP3839347A1 - Carreau de bouclier thermique d'une chambre de combustion - Google Patents

Carreau de bouclier thermique d'une chambre de combustion Download PDF

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Publication number
EP3839347A1
EP3839347A1 EP19218740.9A EP19218740A EP3839347A1 EP 3839347 A1 EP3839347 A1 EP 3839347A1 EP 19218740 A EP19218740 A EP 19218740A EP 3839347 A1 EP3839347 A1 EP 3839347A1
Authority
EP
European Patent Office
Prior art keywords
cooling air
heat shield
combustion chamber
shoulder
shield tile
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.)
Withdrawn
Application number
EP19218740.9A
Other languages
German (de)
English (en)
Inventor
Elke Henschel
Annika Liedtke
Christian Nikasch
Martin Stapper
Michael Winterstein
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 EP19218740.9A priority Critical patent/EP3839347A1/fr
Publication of EP3839347A1 publication Critical patent/EP3839347A1/fr
Withdrawn legal-status Critical Current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
    • F23R3/002—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
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components

Definitions

  • the invention relates to a heat shield tile for use in a combustion chamber of a gas turbine.
  • Heat shield tiles for use in a combustion chamber are well known from the prior art.
  • the EP 3 017 253 B1 a heat shield tile made of a ceramic material, which has an approximately square shape with a hot side facing the interior of the combustion chamber and an opposite cold side. It is provided here that the heat shield tile has a thickness that increases from one side edge to the opposite side edge. On that side edge on which the heat shield tile has a greater thickness, a shoulder is arranged, which is provided to overlap a complementary shoulder in the combustion chamber support structure.
  • the object of the present invention is therefore to reduce the damage caused by the thermal load.
  • the generic heat shield tile is initially used for use in a combustion chamber.
  • the type of combustion chamber in question is initially irrelevant, the use in a gas turbine being particularly appropriate.
  • the heat shield tile has a hot side facing the interior of the combustion chamber, i.e. the combustion chamber, and a cold side on the opposite side. It is intended that the heat shield tile is arranged with the cold side on a support structure of the combustion chamber. Corresponding to the usual use of the heat shield tile in multiple arrangements, it has a longitudinal direction and a transverse direction perpendicular to the longitudinal direction.
  • the hot side of the heat shield tile is connected to the cold side via two opposite longitudinal edges, the longitudinal edges extending approximately in the longitudinal direction, i.e. running along the longitudinal direction.
  • the heat shield tile has a side edge which extends along the transverse direction and also connects the hot side with the cold side. The shape of the longitudinal edges and the side edge is initially irrelevant.
  • the generic heat shield tile has a shoulder which is arranged opposite the side edge on the hot side.
  • the shoulder with the hot side extends beyond the cold side.
  • the shoulder at the end of the heat shield tile has an end surface opposite the side edge and a shoulder surface opposite the hot side offset from the cold side.
  • the shoulder surface is connected to the cold side via a step surface.
  • the heat shield tile has two opposite sides in the step surface Has cooling air pockets. These extend in the transverse direction starting from the opposite longitudinal edges.
  • the cooling air pockets allow cooling air to flow into the area of the step surface, so that as a result the heat shield tile experiences improved cooling in the area of the heel.
  • cooling air pockets adjoin the shoulder surface at least in sections. It is thus made possible that the cooling air flowing through the cooling air pockets can subsequently continue to flow along the shoulder surface.
  • the width of the cooling air pockets viewed in a direction from the hot side to the cold side, continuously decreases from the longitudinal edge in the direction of a center of the heat shield tile. This advantageously promotes the further distribution of the cooling air along the shoulder surface and the step surface, and the strength and stability of the heat shield tile is guaranteed.
  • a preferred length of the respective cooling air pocket in the transverse direction is given if it is at least 0.16 times the length of the step surface in the transverse direction.
  • the cooling air pocket thus has a length in relation to the distance from the cooling air pocket to a center of the heat shield tile of 1: 2.
  • Advantageous cooling can be ensured by using the cooling air pockets. It is particularly advantageous if the length of the cooling air pockets corresponds to at least 0.21 times the length of the step surface.
  • the length of the respective cooling air pocket in the transverse direction is limited to a maximum of 0.32 times the length of the step surface in the transverse direction becomes.
  • the cooling air pocket analogously has a length in relation to the distance between the cooling air pockets and a center of the heat shield tile of 2: 1. This ensures that the stability of the heat shield tile is not inadmissibly impaired due to the cooling air pockets.
  • the length of the cooling air pockets corresponds to a maximum of 0.27 times the length of the step surface.
  • the cooling air guidance can advantageously be improved by furthermore arranging at least one cooling air groove in the step surface. It is particularly advantageous if two cooling air grooves are used. It is provided here that the cooling air groove or the cooling air grooves extend or extend from the shoulder surface to the cold side.
  • At least one cooling air groove is arranged in the shoulder surface.
  • the cooling air groove extends from the step surface to the end surface. It is also particularly advantageous if at least two cooling air grooves are used.
  • cooling air groove or the cooling air grooves it is advantageous if these are or are spaced apart from the cooling air pockets. This ensures that the cooling air flows along the step surface and the shoulder surface and that the cooling air is not diverted too quickly from the cooling air pockets through the cooling air grooves.
  • two cooling air grooves it is also advantageous if these are arranged spaced apart from one another.
  • a certain distance from the cooling air groove to the cooling air pockets is advantageously maintained.
  • the distance between the cooling air groove and the adjacent cooling air pocket as well as a center of the step surface or the shoulder surface is considered.
  • the distance between the respective cooling air groove and the center of the step surface or shoulder surface corresponds to at least 0.3 times the distance between the cooling air groove and the adjacent cooling air pocket. It is particularly advantageous if the distance between the cooling air groove and the center of the step surface corresponds to at least 0.5 times the distance between the cooling air groove and the adjacent cooling air pocket.
  • the distance between the cooling air groove and the center of the step surface or shoulder surface corresponds to a maximum of 0.9 times, particularly preferably a maximum of 0.7 times the distance from the cooling air groove to the adjacent cooling air pocket.
  • the heat shield tile has a recess at least in sections on the longitudinal edges.
  • the recess is spaced apart from the hot side and also spaced apart from the cold side and extends into the heat shield tile. This enables a fastener to be attached.
  • the recess is arranged starting from the cooling air pocket, i.e. starting from the step surface. This enables cooling air to be routed from the recess to the cooling air pocket or vice versa.
  • the embodiment of the heat shield tile according to the invention with the shoulder on the hot side and the cooling air pockets in the step surface can be used with a metallic heat shield tile.
  • At least the generic combustion chamber has a support structure.
  • a plurality of heat shield elements are arranged in several rows on the support structure.
  • the support structure preferably has a rotational shape.
  • a circumferential row of the heat shield elements is now formed by heat shield tiles as described above in the combustion chamber.
  • the use of the heat shield tiles according to the invention increases the service life of the combustion chamber, so that the necessary inspection interval can be extended compared to known designs.
  • the support structure has a circumferential step ring extending in the inner direction of the combustion chamber.
  • the heat shield tiles are arranged on the support structure in such a way that the respective shoulder extends over the step ring.
  • the step ring is arranged at the downstream end of the combustion chamber or the support structure. This leads to an arrangement of the heat shield tiles in which the shoulder is arranged at the downstream end of the heat shield tiles.
  • the heat shield tile can be supported with the step surface on the step ring in a particularly advantageous manner.
  • An advantageous cooling system can be implemented if the cooling air is supplied into the space between adjacent longitudinal edges of the heat shield tile.
  • the cooling air flows along the depressions in the heat shield tile and on through the cooling air pockets to follow to be able to flow along the step surface or the landing surface.
  • FIG. 1 and 2 an exemplary embodiment of a heat shield tile 01 according to the invention is outlined. A perspective view is shown here with a view of the cold side 03. In contrast, the hot side 02 facing the combustion chamber is concealed on the underside.
  • the Figure 3 the heat shield tile 01 likewise in a perspective view, in this case on the hot side 02, with the cold side 03 correspondingly being on the underside which is not visible in this view.
  • the approximately rectangular shape selected in this exemplary embodiment can be seen with the two longitudinal edges 04, which 04 extend along the longitudinal direction.
  • the side edge 05 which 05 extends in the transverse direction transversely to the longitudinal direction.
  • the longitudinal edges 04 and the side edge 05 here connect the cold side 03 with the hot side 02.
  • the depressions 14 running along the longitudinal edges 04, which 14 enable fastening means to be attached, can also be seen.
  • the heat shield tile 01 has a stepped shape with a shoulder 06 arranged on the hot side 02.
  • This 06 forms a shoulder surface 07 opposite the hot side 02, spaced apart from the cold side (approximately in the middle between the hot side and the cold side).
  • the free end of the shoulder 06 opposite the side edge 05, in connection with the hot side 02 and the step surface 07, is formed by the end surface 09.
  • the step surface 08 extends from the cold side 03 to the shoulder surface 07.
  • the selected shape with the shoulder 06 leads to a shape of the heat shield tile 01 with an increasing material thickness as the distance from the hot side 02 to the cold side 03 with a smaller material thickness on the side edge 05 and a larger material thickness on the step surface 08.
  • the shoulder 06 thus makes it possible in particular to cover a step on the support structure 21 located under the heat shield tile 01.
  • Essential for the present invention is the introduction of two opposite cooling air pockets 11, which 11 extend starting from the step surface 08 to the opposite side edge 05 and starting from the respective longitudinal edge 04 to the center of the heat shield tile 01. These cooling air pockets 11 promote the cooling air guidance with a better distribution of the cooling air along the step surface 08 and the shoulder surface 07.
  • the cooling air pockets 11 are arranged directly adjacent to the shoulder surface 07. It can also be seen that the cooling air pockets 11 in this exemplary embodiment extend along the transverse direction over more than a quarter but over slightly less than a third of the width of the heat shield tile 01 from one longitudinal edge 04 to the opposite one Longitudinal edge 04 extend. In contrast, the width (in the direction from the hot side 02 to the cold side 03) of the cooling air pockets 11 decreases starting from the respective longitudinal edge 04 towards the center.
  • cooling air grooves 12 in the shoulder surface 07 can also be seen, which in this exemplary embodiment extend from the step surface 08 to the inner surface 09 and are spaced apart from the center of the heat shield tile 01 and spaced apart from the cooling air pockets 11.
  • the heat shield tile 01 is sketched again, this view showing the heat shield tile 01 in the side view with a view of a side edge 04.
  • the arrangement of the heat shield tile 01 on a support structure 21 of a combustion chamber is also shown.
  • the approximately wedge-shaped shape with the increasing material thickness can be seen as the distance from the hot side 02 to the cold side 03.
  • the side edge 05 is on the upper side and the shoulder 06 with the end surface 09 on the opposite side is on the lower side Bottom.
  • the heat shield tile 01 rests with the step surface 08 on a step ring 22 of the support structure 21.
  • the shoulder 06 covers the step ring 22.
  • the arrangement of a further heat shield element above the heat shield tile 01 on the support structure 21 is shown schematically.
  • the cooling air pocket 11 can be seen in the side view. This 11 extends from the recess 14 in the side edge 04 in the transverse direction into the heat shield tile 01.
  • the combustion chamber with the support structure 21 usually has a rotational shape and thus the heat shield tiles 01 resting on the support structure 21 also in the transverse direction of the heat shield tiles 01 have a partially rotational shape.
  • the hot side 02 and the cold side 03 as well as the shoulder surface 07 are generally arched and not - as shown here in a simplified manner - designed to be flat.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP19218740.9A 2019-12-20 2019-12-20 Carreau de bouclier thermique d'une chambre de combustion Withdrawn EP3839347A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP19218740.9A EP3839347A1 (fr) 2019-12-20 2019-12-20 Carreau de bouclier thermique d'une chambre de combustion

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP19218740.9A EP3839347A1 (fr) 2019-12-20 2019-12-20 Carreau de bouclier thermique d'une chambre de combustion

Publications (1)

Publication Number Publication Date
EP3839347A1 true EP3839347A1 (fr) 2021-06-23

Family

ID=69005262

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19218740.9A Withdrawn EP3839347A1 (fr) 2019-12-20 2019-12-20 Carreau de bouclier thermique d'une chambre de combustion

Country Status (1)

Country Link
EP (1) EP3839347A1 (fr)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1022437A1 (fr) * 1999-01-19 2000-07-26 Siemens Aktiengesellschaft Elément de construction à l'usage d'une machine thermique
US20070151249A1 (en) * 2004-01-27 2007-07-05 Claudia Barbeln Heat shield
US20150285496A1 (en) * 2012-09-21 2015-10-08 Siemens Aktiengesellschaft Device for cooling a supporting structure of a heat shield, and heat shield
EP3017253B1 (fr) 2013-09-11 2017-04-26 Siemens Aktiengesellschaft Bouclier thermique céramique pour une chambre de combustion de turbine à gaz, chambre de combustion pour une turbine à gaz et procédé
EP3017252B1 (fr) * 2013-07-03 2017-08-30 Ansaldo Energia S.p.A. Tuile de revêtement de chambres de combustion, en particulier pour centrale à turbine à gaz et chambre de combustion comprenant ladite tuile

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1022437A1 (fr) * 1999-01-19 2000-07-26 Siemens Aktiengesellschaft Elément de construction à l'usage d'une machine thermique
US20070151249A1 (en) * 2004-01-27 2007-07-05 Claudia Barbeln Heat shield
US20150285496A1 (en) * 2012-09-21 2015-10-08 Siemens Aktiengesellschaft Device for cooling a supporting structure of a heat shield, and heat shield
EP3017252B1 (fr) * 2013-07-03 2017-08-30 Ansaldo Energia S.p.A. Tuile de revêtement de chambres de combustion, en particulier pour centrale à turbine à gaz et chambre de combustion comprenant ladite tuile
EP3017253B1 (fr) 2013-09-11 2017-04-26 Siemens Aktiengesellschaft Bouclier thermique céramique pour une chambre de combustion de turbine à gaz, chambre de combustion pour une turbine à gaz et procédé

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