EP3333484A1 - Composant en forme de plaque d'une turbine à gaz - Google Patents

Composant en forme de plaque d'une turbine à gaz Download PDF

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Publication number
EP3333484A1
EP3333484A1 EP17205686.3A EP17205686A EP3333484A1 EP 3333484 A1 EP3333484 A1 EP 3333484A1 EP 17205686 A EP17205686 A EP 17205686A EP 3333484 A1 EP3333484 A1 EP 3333484A1
Authority
EP
European Patent Office
Prior art keywords
plate
shaped component
cooling air
edge strip
base body
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.)
Granted
Application number
EP17205686.3A
Other languages
German (de)
English (en)
Other versions
EP3333484B1 (fr
Inventor
Dr. Kay HEINZE
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP3333484A1 publication Critical patent/EP3333484A1/fr
Application granted granted Critical
Publication of EP3333484B1 publication Critical patent/EP3333484B1/fr
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
    • F23R3/002—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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
    • 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
    • F23R2900/00018—Manufacturing combustion chamber liners or subparts
    • 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 invention relates to a plate-shaped component of a gas turbine according to the features of the preamble of claim 1.
  • the invention also relates to a gas turbine with a plate-shaped component.
  • the invention relates to a plate-shaped component, which is formed, for example, in the form of a combustion chamber shingle.
  • the plate-shaped component has a base body on which at least one edge region is provided.
  • This edge region is designed in the form of a peripheral strip, which extends substantially to the surface of the main body.
  • the edge strip has a thickness which differs from the thickness of the base body.
  • the edge strip is formed with a greater thickness than the main body itself.
  • Such a plate-shaped component in the form of a combustion chamber shingle is from the WO 2015069466 A1 previously known. Furthermore, on the EP 2 873 921 A1 Referenced.
  • Components of the type described are preferably produced by means of an additive manufacturing method, for example by means of a laser deposition welding method or by means of DLD direct laser deposition.
  • the respective component is built up from a powder supply layer by layer by melting the powder. This leads to local solidification of the respective molten layer. Thus, complex 3D geometries can be generated.
  • the invention has for its object to provide a plate-shaped component, in particular for a gas turbine, in particular in the form of a combustion chamber shingle, which avoids the disadvantages of the prior art with a simple structure and simple, cost-effective manufacturability and has favorable material properties.
  • an integrally connected with the base body and the skirting support body is arranged between the edge strip and the base body, which has a substantially triangular cross-section and which is provided with a plurality of slot-like recesses.
  • the support body according to the invention which is arranged between the base body and the skirt, results in a usually vertical orientation of the body in the additive manufacturing process, an increasing transition from the wall thickness of the body to the skirt or vice versa. Sudden geometric changes, which could lead to residual stresses and cracking, are thus avoided.
  • the support body according to the invention has a plurality of slot-like recesses, so that a substantially rib-like shape of the support body results. Overall, this leads with suitable dimensioning to a low accumulation of material at the transition between the body to the skirt. As a result, not only occurring voltage spikes are avoided, but also the possibility of effective cooling is created. This is possible in particular in that at least one cooling air hole is formed in the respective slot-like recess.
  • each slot-like recess in each case a body penetrating the cooling air hole is arranged.
  • the component according to the invention is particularly suitable when using brittle materials which have high requirements in terms of stress distribution and material strength.
  • the invention thus provides a transition between components of different thickness or different volume, which allows the production of the component by means of an additive manufacturing process.
  • the individual slot-like recesses can be geometrically designed in a suitable manner. The same applies to the preferred implementation of the cooling air holes. It is understood that the width of the recesses and the respective remaining width of the region of the support body between the recesses can also be adapted to the component geometries, such as the dimensioning and geometry of the cooling air hole. It is also possible to provide a plurality of cooling air holes in a recess.
  • the remaining between the recesses strip-shaped areas of the support body lead to a reduction of residual stresses along the longitudinal side of the billet in the additive construction of the shingle.
  • the occurrence of residual stresses can thereby be avoided, especially in the case of brittle materials. The risk of cracking is thus significantly reduced.
  • the plate-shaped component according to the invention can be optimized with regard to cooling.
  • the additive manufacturing process makes it possible to design the cooling holes differently over their length, for example to change the cross section. All this means that a sufficient volume of cooling air can be directed to the rear edge of the base body of the plate-shaped component opposite the edge strip.
  • the possibility of making the cooling holes variable in their longitudinal extent, arcuate or coiled or meandering forms of cooling air holes can be realized. This leads to a more effective cooling.
  • the plate-shaped component comprises additional cooling air holes, which extend through the edge strip and emanate from the slot-shaped recess.
  • the additional cooling air holes are therefore edge air holes, which lead cooling air through the edge strip from the recess to the outside.
  • the additional cooling air holes may preferably have a widening cross section in the direction of flow, in particular have a conically widening cross section.
  • the additional cooling air holes act as a diffuser.
  • Particularly preferred is a smallest cross section of the additional cooling air hole at the entrance to the edge strip or adjacent to Entry into the edge strip, ie in a range of 10% of a total length of the additional cooling air hole through the edge strip, available.
  • cooling in the region of the edge strip of the plate-shaped component can be effected exclusively by the slot-shaped recesses or by cooling air holes which are formed in the base body of the plate-shaped component or by additional cooling air holes which are formed in the edge strip of the plate-shaped component or by a combination of the additional cooling air holes through the skirting and the cooling air holes through the body.
  • variants can be used with no cooling air hole at the recess, a cooling air hole in the edge strip or the body or two cooling air holes in the skirt and the body.
  • the recess is formed symmetrically to the center plane of the cooling air hole. This results in uniform stress distributions in the region of the recess and the adjacent regions of the support body. Furthermore, the supply of cooling air is optimized in the cooling air hole.
  • the slot-like recesses of the support body may be formed in a favorable embodiment of the invention so that the walls of the recess adjacent to the surface of the body on both sides initially have a rectilinear course of the wall, which merges into a rounded wall to form an arcuate structure in the upper part of the slot-like recess , It is particularly advantageous if the rounded wall course has a radius which is between 0.1 to 2 times, in particular 1 to 2 times, the width of the recess. In a particularly favorable development, it is provided that the rounded wall profiles form an angle between 45 ° and 120 °. As a result, the spike arc-like contour of the recesses in the side view is realized particularly effective.
  • the spacing of adjacent recesses may, in the longitudinal direction of the edge strip, correspond to greater than or equal to half the width of the recesses.
  • substantially equidistant recesses and remaining chamfer-like areas of the support body are provided alternately along the edge strip.
  • the support body itself which forms a chamfer-like transition between the base body and the edge strip, may have an angle with respect to its surface to the surface of the base body between 30 ° and 60 °. An amount of 45 ° is preferred.
  • the central axis of the cooling air hole at right angles or at an obtuse angle to the surface of the body, ie in a range of 90 ° to 180 °, to arrange.
  • preferred cooling effects can be achieved, in particular, on regions of the edge strip or of the base body subjected to high thermal stress.
  • FIG. 1 shows a perspective view in a partial view of a first embodiment of a plate-shaped component according to the invention, which is designed in the form of a combustion chamber shingles of a gas turbine.
  • the plate-shaped component has a main body 1, which is designed as a flat plate.
  • the base body 1 has a surface 6, which faces away from a combustion chamber interior of a gas turbine engine.
  • the surface 6 is the cold surface of the plate-shaped member (combustion chamber shingles).
  • a plurality of effusion cooling holes are formed, as known from the prior art.
  • the main body 1 has a thickness d1.
  • a skirt 2 which has a thickness d2.
  • the thickness d1 is measured from the surface 6 of the main body 1 to the back thereof. In the same direction, the thickness d2 of the skirt 2 is defined.
  • the edge strip 2 which is integrally formed by means of an additive method with the base body 1, is supported by a support body 3. This points, as this is from the Fig. 2 results in a substantially triangular cross section. Over the length of the support body it is provided with a plurality of recesses 4. The between the recesses 4 remaining areas of the support body 3 are thus strip-shaped or strip-shaped.
  • each recess 4 at least one cooling air hole 5 is provided which extends from the recess 4 to the back of the main body 1, analogous to the Effusionskühllöchern 10th
  • the free surface of the support body 3 has to the surface 6 of the base body 1 at an angle ⁇ , which may be between 30 ° and 60 °. A value of 45 ° is preferred.
  • the Fig. 3 shows a plan view of the arrangement according to the Fig. 1 and 2 , It can be seen that the recess 4 has a width l3.
  • the side walls of the recess 4, which in Fig. 3 are designated as l1 and l2, each have a rectilinear course of the wall 7 and go into a rounded wall 8, the radius of each with r1 and r2 in Fig. 3 is clarified.
  • the two rounded wall curves 8 meet at an angle ⁇ . This can be between 45 ° and 120 °.
  • the length of the rectilinear wall courses 7 (11 or 12) is preferably the same and ⁇ 0 mm.
  • the radii r1 and r2 are also equal and are 0.1 to 2 times the width l3 of the recess 4.
  • Both the straight wall profiles 7 with the lengths l1 and l2 and the rounded wall profiles 8 with the radii r1 and r2 are not necessarily necessary for the invention, other wall profiles can be realized to form the recess 4. Both the lengths l1 and l2 and the radii r1 and r2 can deviate from one another at the specified intervals. Also, it is not mandatory that the recess 4 is arranged symmetrically to a median plane of the cooling air hole 5.
  • the Fig. 3 shows the positioning of the cooling air hole 6 with its central axis 9.
  • the recesses 4 thus form a support structure, which is defined by two rounded or arcuate wall portions, between which the individual cooling air holes 5 are arranged.
  • the production of the component according to the invention by an additive method is usually carried out with a vertical orientation of the body 1. If this is provided on all sides with a skirt, a skirt with the thickness d2 is first constructed. The transition to the base body 1 with a thickness d1 is carried out continuously by the respective support body 3, which is provided with the recesses 4.
  • the component according to the invention can be provided with a rim 2 at all its edges.
  • the plate-shaped base body 1 is not limited to a flat plate, it may also be curved or double-curved.
  • Fig. 4 schematically shows a simplified plan view of a slot-like recess according to a second embodiment of the invention.
  • the second embodiment essentially corresponds to the first embodiment, wherein in addition in each case an additional cooling air hole 15 is provided.
  • the additional cooling air hole 15 extends from the slot-like recess 4 through the edge strip 2 of the plate-like component and opens on the outside of the edge strip.
  • a flow cross section of the additional cooling air hole in the edge strip 2 preferably changes Fig. 4 shown, the additional cooling air hole 15 is formed as the diffuser, wherein the narrowest cross section is located at the entrance to the skirt 2.
  • the additional cooling air hole 15 is preferably rectilinear.
  • the additional cooling air hole 15 may also have a curved course in the flow direction. Due to the additional cooling air hole 15, the edge strip 2 can thus additionally be cooled. The diffuser formation of the additional cooling air hole 15 reduces the speed of the cooling air, whereby a cooling effect can be increased.
  • Fig. 5 shows a fifth embodiment of the invention, which, in contrast to the first embodiment, no cooling air holes 5, which are arranged on the slot-like recess 4.
  • Fig. 6 shows a fourth embodiment of the invention.
  • the fourth embodiment corresponds essentially to the second embodiment, wherein, in contrast to the second embodiment, no cooling air holes 5 are provided by the base body 1, which are arranged at the bottom of the recess 4.
  • the slot-shaped recess 4 is cooled only by the additional cooling air holes 15, which extend through the edge strip 2.
  • the additional cooling air hole 15 through the skirt 2 is formed as a diffuser as in the second embodiment. It should be noted, however, that other geometric shapes may be provided for the additional cooling air hole 15, for example a constant cross section over the flow length of the additional cooling air hole 15.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP17205686.3A 2016-12-09 2017-12-06 Bardeau de chambre de combustion d'une turbine à gaz Active EP3333484B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102016224632.1A DE102016224632A1 (de) 2016-12-09 2016-12-09 Plattenförmiges Bauteil einer Gasturbine sowie Verfahren zu dessen Herstellung

Publications (2)

Publication Number Publication Date
EP3333484A1 true EP3333484A1 (fr) 2018-06-13
EP3333484B1 EP3333484B1 (fr) 2020-07-22

Family

ID=60654704

Family Applications (1)

Application Number Title Priority Date Filing Date
EP17205686.3A Active EP3333484B1 (fr) 2016-12-09 2017-12-06 Bardeau de chambre de combustion d'une turbine à gaz

Country Status (3)

Country Link
US (1) US10753612B2 (fr)
EP (1) EP3333484B1 (fr)
DE (1) DE102016224632A1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3097029B1 (fr) * 2019-06-07 2021-05-21 Safran Helicopter Engines Procédé de fabrication d’un tube à flamme pour une turbomachine
CA3141179A1 (fr) * 2019-06-07 2020-12-10 Safran Helicopter Engines Procede de fabrication d'un tube a flamme pour une turbomachine

Citations (3)

* 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
EP2927592A1 (fr) * 2014-03-31 2015-10-07 Siemens Aktiengesellschaft Élément de bouclier thermique, bouclier thermique et turbomachine
EP3056813A1 (fr) * 2015-02-12 2016-08-17 Rolls-Royce Deutschland Ltd & Co KG Joint pour un interstice marginal entre les bardeaux d'effusion d'une chambre de combustion de turbines a gaz

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FR2668246B1 (fr) * 1990-10-17 1994-12-09 Snecma Chambre de combustion munie d'un dispositif de refroidissement de sa paroi.
US6032457A (en) * 1996-06-27 2000-03-07 United Technologies Corporation Fuel nozzle guide
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EP1672281A1 (fr) 2004-12-16 2006-06-21 Siemens Aktiengesellschaft Elément de protection thermique
US7681398B2 (en) * 2006-11-17 2010-03-23 Pratt & Whitney Canada Corp. Combustor liner and heat shield assembly
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EP2182285A1 (fr) * 2008-10-29 2010-05-05 Siemens Aktiengesellschaft Pièce du brûleur pour une chambre de combustion d'une turbine à gaz et turbine à gaz
US7980821B1 (en) * 2008-12-15 2011-07-19 Florida Turbine Technologies, Inc. Turbine blade with trailing edge cooling
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WO2014163694A2 (fr) * 2013-03-13 2014-10-09 Moody Jack K Agencement de trou de refroidissement à tranchée pour une ailette composite à matrice céramique
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Patent Citations (3)

* 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
EP2927592A1 (fr) * 2014-03-31 2015-10-07 Siemens Aktiengesellschaft Élément de bouclier thermique, bouclier thermique et turbomachine
EP3056813A1 (fr) * 2015-02-12 2016-08-17 Rolls-Royce Deutschland Ltd & Co KG Joint pour un interstice marginal entre les bardeaux d'effusion d'une chambre de combustion de turbines a gaz

Also Published As

Publication number Publication date
EP3333484B1 (fr) 2020-07-22
DE102016224632A1 (de) 2018-06-14
US10753612B2 (en) 2020-08-25
US20180163964A1 (en) 2018-06-14

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