US2919549A - Heat-resisting wall structures - Google Patents

Heat-resisting wall structures Download PDF

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Publication number
US2919549A
US2919549A US484492A US48449255A US2919549A US 2919549 A US2919549 A US 2919549A US 484492 A US484492 A US 484492A US 48449255 A US48449255 A US 48449255A US 2919549 A US2919549 A US 2919549A
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Prior art keywords
wall
pieces
flanges
mosaic
heat
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Expired - Lifetime
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US484492A
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English (en)
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Haworth Lionel
Shire Ralph John
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Rolls Royce PLC
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Rolls Royce PLC
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/16—Two dimensionally sectional layer
    • Y10T428/163—Next to unitary web or sheet of equal or greater extent
    • Y10T428/164—Continuous two dimensionally sectional layer
    • Y10T428/166—Glass, ceramic, or metal sections [e.g., floor or wall tile, etc.]

Definitions

  • This invention relates to heat-resisting wall structures employed to define a space wherein fuel is burnt, or to define a duct wherein hot gas may flow, for example in a gas-turbine engine.
  • the invention has for an object to provide an improved heat-resisting wall construction whereby the possibility of failure of the wall, for example due to overheating or due to thermal shock, is reduced.
  • a heat-resisting wall structure defining a space wherein fuel is burnt is formed at least in part by a multiplicity of pieces arranged mosaicwise with their edges unjoined but close 'tO one another, said pieces being supported individually in juxtaposition from support structure externally of said space.
  • the pieces are supported from the support structure through means aflording paths of restricted heat conductivity.
  • the support structure comprises a substantially continuous wall, and the pieces provide a protective wall spaced'away from the continuous wall.
  • the support structure is of skeleton form, for example comprising a plurality of rings arranged in axially spaced relation on rod elements, the pieces of the mosaic wall being mounted individually on the skeleton support structure.
  • the heat-resisting wall structure is accommodated in a casing providing a passage for the flow of cooling air externally of the space defined by the heatresisting wall structure.
  • a support structure provided by a substantially continuous Wall, provision may be made for creating a flow of cooling air between the continuous wall and the wall constituted by the pieces.
  • the pieces are of regular shape such as triangular, rectangular, square or hexagonal, so that when they are arranged mosaicwise they form an area of wall without large gaps between the pieces.
  • the pieces may be made either separately from the support structure and then be mounted individually thereon, or they may be made integral withthe support structure.
  • the pieces may be connected with the support struc ture each by one or more stalks or stems which have individually a small cross-sectional area at right angles to the direction of heat conduction as compared with the surface area of the piece.
  • a single stalk or stem is employed for each piece.
  • each piece may be connected with the support structure through a narrow Web; for instance a heat-resisting structural wall structure .may be formed from lengths or turns of H-section strip, the lengths or turns of the strip being joined by welding together the longitudinal edges of adjacentflanges to form a continuous external ,supportwall,andtheother flanges being slotted to divide ice the flange into a number of pieces, and the web of the H-section which connects the flanges also being slotted to divide the web into a number of sections, each section joining a single mosaic piece to the continuous structural wall.
  • a heat-resisting structural wall structure may be formed from lengths or turns of H-section strip, the lengths or turns of the strip being joined by welding together the longitudinal edges of adjacentflanges to form a continuous external ,supportwall,andtheother flanges being slotted to divide ice the flange into a number of pieces, and the web of the H-section which connects the flanges also being slotted to divide the web
  • the wall portion may have apertures therein to admit secondary or tertiary air into the flame tube. Alternatively or additionally air may be metered to the combustion space through the gaps between the mosaic pieces.
  • the relative restrictions of the apertures in the wall structure and the gaps between the mosaic pieces will preferably be selected so that the pressure between the inner and outer wall structures lies between the pressure outside the wall portion and the pressure within the flame tube.
  • stalks or stems by which the mosaic pieces are connected to the outer support structure may be formed with ducts extending through them to permit the passage of a cool fluid from outside the wall portion to within the heated space and also to reduce the effective cross-sectional area available for conduction.
  • Figure 1 illustrates in perspective a section of a flame tube wall
  • Figures la, 1b, 1c, 1d show alternative methods to that illustrated in Figure 1 for securing parts of the wall structure together
  • Figures 1e, 1 and lg show alternative forms for parts of the protective screen
  • Figure 2 shows an alternative form of wall structure
  • FIG. 2a illustrates the method by which it may be made
  • Figure 3 illustrates yet another form for a wall structure
  • Figure 3a illustrates a method by which it may be formed
  • Figure 4 illustrates yet another form of a wall structure
  • Figure 5 illustrates partly in section a portion of a flame tube with a heat-resisting wall portion made in yet another form according to the invention
  • Figure 5a illustrates a detail of Figure 5
  • Figure 6 illustrates diagrammatically a flame tube having a support structure of skeleton form with sheetmetal Wall pieces supported thereon
  • Figure 6a is a section on the line a-a of Figure 6,
  • Figure 6b is an enlarged view of a portion of the section shown in Figure 6a
  • Figures 7 and 7a show a variant of the construction shown.
  • Figures 6, 6a and 6b in which the wall pieces are provided with interlocking tongues and grooves,
  • Figure 8 is a view corresponding to Figure 6 of another construction of flame tube
  • Figure 8a is a part of Figure 8 to a larger scale
  • Figure 8b is a section on bb of Figure 8,
  • Figure 8c is a view on the outside of the fiame tube of Figure 8.
  • Figure 9 is a part of another form of flame tube.
  • the heat-resisting wall structure forms part of a flame tube of a gas-turbine engine combustion equipment which comprises an outer wall 10 which in use will provide one boundary for the air passage between the air casing 10a of the combustion equipment and the flame tube.
  • the outer wall is substantially continuous but may have formed in it apertures such as the apertures 11 which may serve for the passage of ignition devices, fuel injectors of flame tube interconnectors.
  • the apertures 11 may be of any convenient shape such, for example, as shown in Figures 1e, 1 and lg according to the purpose which they are to serve.
  • the heat-resisting wall structure also comprises an inner wall structure affording a protective screen for the outer wall which supports it.
  • the inner wall comprises a mosaic of pieces 12 which are spaced away from the outer wall and which in use afford a boundary for the combustion space of the flame tube.
  • Each piece 12 is supported from the outer wall 10 by an individual stalk or stem 13 which may take a number of convenient forms.
  • the stalk or stem 13 is formed integral with its associated mosaic piece 12 and projects through an aperture in the outer wall 10, which aperture has a peripheral neck 14 produced in the aperture-forming operation and the stalk or stem 13 is welded to the outer wall 10 on the side thereof remote from the mosaic pieces 12.
  • the stalk or stem 13 is similar to the stalk or stem shown in Figures 1, 1a and lb, but in this case is copper brazed to the outer wall 10 on the side thereof adjacent the combustion space of the flame tube.
  • the stalk or stem 13 has a rivet connection 15 with the outer wall 10.
  • the stalk or stem 13 may be solid as shown in Figure la or may have as shown in Figure 1 a drilling 16 through it for the passage of cooling air, or may have a venturishape passage 17 through it as shown in Figures 1b, la and 1d.
  • the mosaic pieces are individually substantially smaller in area than the outer wall.10, so that a multiplicity of mosaic pieces 12 is required to form the protective screen for the outer wall portion 10.
  • the pieces 12 are conveniently made of regular shape such as square as shown in Figures 1 and 1e, or hexagonal as shown in Figure 1f, or triangular as shown in Figure lg, so that their edges may be readily brought close together and so that the spacing of the edges may be readily maintained equal.
  • a corresponding aperture is formed in the inner wall structure, for instance by omitting one or more of the mosaic pieces 12.
  • the aperture in the outer wall 10 is larger than that left by omission of the mosaic pieces 12.
  • the stalks or stems 13 have a small cross-sectional area as compared with the area of the pieces 12 and so afford a relatively low heat conductivity path between the pieces 12 of the inner wall structure and the outer wall 10.
  • the mosaic pieces 12 for forming the inner wall structure are made separately from the outer wall 16
  • the mosaic pieces 12 may be formed from a heatresistant material, for instance from the metal marketed under the trademark Nimonic or from a ceramic
  • the outer wall may be formed from a material such as stainless steel or mild steel selected according to the temperature it is likely to experience in operation.
  • the material is selected so that the conductivity of the outer wall is high.
  • FIG. 2 and 2a there is illustrated a method of producing a wall structure whereof the mosaic pieces forming the inner wall structure are integral with the outer supporting wall.
  • a thick plate is taken and a series of drillings made in the thickness of the plate parallel to the surfaces thereof, there being for example one set of drillings 20 in one direction and produced as by a drill 20a, and a second set of drillings 21 at right angles to the first set of drillings 20 and produced as by a drill 21a.
  • One of the surface portions is now machine to produce a series of slots 23 parallel to the axes of the drillings 20 and contained in planes through the respective axes of the drillings 20 and at right angles to the surfaces of the plate, and a second series of slots 24 parallel to the axes of the drillings 21 and contained in planes through these axes and at right angles to the surfaces of the plate.
  • the machined surface is thus divided up into a series of square pieces 25 whereof the edges are unjoined but close to one another and which are joined to a substantially continuous wall 26 afforded by the unmachined surface portion by the stalks or stems 22.
  • the spacing of the drillings 21 is the same as the spacing of the drillings 20, but clearly if the spacings of the drillings 20 and 21 difler, then the pieces 25 will be rectangular and if the inclination of the drillings 21 with respect to the drillings 20 is other than a right angle, then the pieces 25 will be of parallelogram form. If, say, triangular pieces are required, then a further set of drillings will be necessary.
  • the heat-resisting wall structure is formed from extruded metal strip of H-section and lengths of the strip are brought into abutment over the longitudinal edges of one set of flanges 3t) and are welded together over these flanges.
  • the other set of flanges 31 are left unconnected and a series of saw-cuts 32 are made across these flanges at right angles to the longitudinal axes of the lengths of H-section strip so as to divide the flanges 31 into a number of pieces 33 which are unconnected at their edges.
  • a series of drillings are made by a drill 34 at right angles to the length of the strips so as to divide the webs 35 joining the flanges 30, 31 into a number of individual web pieces each corresponding to a single mosaic piece 33.
  • the holes 36 made by the drill 34 have their axes parallel to and in the same planes as the series of sawcuts 32.
  • the structure has a substantially continuous support wall formed by the flanges 30 and an inner wall formed by the pieces 33 which protects the structural wall.
  • FIG 4 there is illustrated another arrangement and in this arrangement there is first produced a sheet 40 having thereon a series of parallel fins which are slotted at right angles to their length, as indicated at 41, to produce a series of short web elements 42.
  • This sheet has attached to it a second sheet 43 as by welding and a series of intersecting slots 44 are then machined in the sheet 40 to produce mosaic pieces 45, each mosaic piece 45 being associated with a web element 42.
  • One set of the slots 44 is machined parallel to but between the web elements 42, and a second series of slots is machined at right angles to the web elements and adjacent the slots 41.
  • FIG. 5 and 5a there is illustrated the inlet end and intermediate portion of a flame tube of gas-turbine engine combustion equipment, whereof part of the wall of the flame tube is a mosaic wall structure in accordance with the invention.
  • the inlet end is shown at 60 and the outlet end at 61.
  • the intermediate portion comprises a skeleton support structure provided by a number of rods 62 which are welded or otherwise secured at their ends to ring members 63 and 64 supported respectively by the inlet end 60 and the outlet end 61.
  • the rods 62 extend parallel to the axis of the flame tube and are disposed on a circle having its centre on the said axis.
  • the spacing of the rods intermediate the end portions 60 and 61 is maintained by rings 65 which have apertured lugs 65a through which the rods 62 pass.
  • the rings 65 are ,welded or otherwise secured to the rods 62.
  • the rods 62 and rings 65 thus form a skeleton support structure providing a rigid connection between the inlet and outlet portions 66 and 61.
  • Sheetmetal wall pieces 66 are supported on this skeleton structure, being of substantially rectangular form and having tabs upstanding from their outer surfaces and hooked or bent over the rods 62. At one end of each wall piece there is a single central tab, whilst at the other end there are two such tabs spaced apart. In the assembly the first tab engages a rod 62 between the two tabs of the adjacent wall piece. A suitable tool is used for turning over the end portions to engage the rods 62.
  • an interconnector pipe 67 is provided, this pipe being supported on a wall piece 68 the area of which is approximately four times the area of a standard wall piece.
  • one of the rods 62 ' is discontinued, whereby the wall piece 68 spans an extended area, being connected to the support structure in a manner similar to the standard wall pieces.
  • the construction described provides a wall structure in which the individual pieces have relative freedom for thermal expansion, whilst the support structure lies externally of the fuel burning space and is therefore relatively cool.
  • such structure is in the installation of the flame tube in a gas-turbine engine subjected to a cooling air flow which passes between the flame tube wall and an outer air casing containing the flame tube.
  • each piece 70 is formed with a lug portion 7% which is drilled to receive a rod 62.
  • the edge of the wall piece 70 adjacent the lug 76a is grooved at 70b to receive a tongue formation on the edge of the adjacent wall piece.
  • the assembly may thus for example involve securing the rods 62 to one end portion, e.g.
  • the wall pieces may overlap in the axial sense by providing an undercut on one wall piece engaged by a protruding tongue on the co-operating wall piece of the adjacent row. In this manner the leakage flow of gas through the wall may be reduced.
  • FIG. 8a, 8b, 80 there is illustrated another view of flame tube for use in gas-turbine engine combustion equpment.
  • the outer aircasing is also shown at Itib.
  • the construction is similar to that shown in Figures 5 and 5a, in that it is made from H-section strip but in this case instead of the strip being wound spirally there are a number of lengths'of strip arranged side by side to produce a cylinder and the strips are joined together over the longitudinal edges of theirouter flanges 30 as by welding.
  • the inner flanges of the lengths of strip are left unconnected along their edges and are divided by circumferentially extending slots 32a into a plurality of mosaic pieces 33.
  • the slots are extended radially outwards across the webs 35 which join the mosaic pieces 33 and the outer flanges 30.
  • the lengths of strip Adjacent their upstream ends, the lengths of strip have their inner flanges and the webs removed to leave portions 30a which are curved inwardly to form part of the entry section of the flame tube.
  • Air may be admitted to the spaces between the webs 35 by means of holes 37 in the outer flanges 30.
  • the spaces 35 may be divided up into a number of axially separated sections by forming circumferential slots in the outer flanges 30 to extend radially inwards through the webs 35 and by welding annuli 38 in position in the slots so as to form between the axially separated sections.
  • Holes may be provided through the heat-resisting wall structure for the admission of air, for the interconnection of flame tubes by balance pipes, or for other purposes. These holes are conveniently fitted with liners, for instance as indicated at 39, and the sleeves may be of greater diameter where they are secured to the outer flanges 30 of the lengths of H-section strip than adjacent the mosaic pieces 33.
  • H-section rings are employed and these may have attached to them, as by welding, in abutment with their outer flanges 71 tubular parts 72.
  • the inner flanges of the H-section rings are divided up into mosaic pieces as indicated at 73, and the webs joining the outer flanges 71 with the mosaic pieces 73 are slotted as indicated at 74 so that each mosaic piece 73 is supported by an individual web section.
  • the central tubular part 72 may of course be replaced by other H-section rings.
  • Holes 75 are provided in the outer flanges 71 to allow air to flow to between the flanges 71 and mosaic pieces 73.
  • size of the mosaic parts will be determined in any particular case and ordinarily the size will be a compromise between conflicting design considerations.
  • the edges of the mosaic pieces will tend to droop under their own weight when very hot if made larger than a certain size, and from this point of view the mosaic pieces should be kept as small as possible.
  • the mosaic pieces should be kept as large as possible.
  • a square is thought to be a suitable size for the mosaic pieces, and 0.15" is thought to be a suitable spacing for the mosaic pieces from the outer wall.
  • flame tubes manufactured in accordance with this invention will have an increased life, which is desirable since in modern gasturbine engines a flame tube has a shorter life than other parts such as the highly stressed moving blades of a turbine.
  • the supply of secondary and tertiary air into the combustion space is conveniently effected through the heatresistant wall from the space immediately within the air casing structure.
  • apertures are formed in the outer support wall structure of such size in relation to the gaps between the mosaic pieces, that the pressure between the outer wall and protective screen is intermedate thg pressures outside the outer wall and within the flame tu e.
  • the mosaic screen connected to the outer wall by stalks, stems or narrow webs has the eifect of prevent-- vection and substantially reduces the rate at which heat can be conveyed to the outer wall by conduction.
  • the outer wall of the flame tube may be made thinner and of a material appropriate to the much lower temperature that it will experience in operation.
  • Another advantage of the arrangement of the invention is that if a piece of the protective screen breaks away and is carried through the turbine, the possibility of damage to the turbine is low because of the small size of the mosaic pieces.
  • Gas-turbine engine combustion equipment comprising an outer air casing structure which contains a flame tube made up from a set of lengths of H-section strip which strip comprises a pair of end flanges interconnected by a web formation, the one end flanges affording a first wall of the flame tube which defines a combustion space and the other end flanges being joined together longitudinally to provide a continuous support wall on the side of the first wall remote from the combustion space, pressure cooling air being fed to the spaces between the walls, said one end flanges being slotted transversely to provide a multiplicity of relatively small pieces arranged mosaicwise and having surfaces thereof facing the combustion space contained in a substantially continuous geometrical surface, the edges of adjacent pieces being unjoined but close to one another, and at least those edges of adjacent pieces which extend in directions transversely to the general direction of gas flow through the combustion equipment affording between them restricted air leakage flow passages into the combustion space, whereby the air leaking through said passages flows substantially over the whole of the surface of said second wall facing the combustion space.
  • Gas-turbine engine combustion equipment as claimed in claim 1 comprising holes in said other end flanges to place the spaces between the webs in communication with the exterior of said other end flanges, for the flow of cooling gas from the space immediately within the outer air casing structure to the combustion space.
  • Gas-turbine engine combustion equipment comprising an outer air casing structure which contains a flame tube made up from turns of H-section strip which strip comprises a pair of end flanges interconnected by a web formation, the one end flanges affording a first wall of the flame tube which defines a combustion space and the other end flanges aflording a continuous support wall on the side of the first wall remote from the combustion space, pressure cooling air being fed to the spaces between the walls, said one end flanges being slotted transversely to provide a multiplicity of relatively small pieces arranged mosaicwise and having surfaces thereof facing the combustion space contained in a substantially continuous geometrical surface, the edges of adjacent pieces being unjoined but close to one another, and at least those edges of adjacent pieces which extend in directions transversely to the general direction of gas flow through the combustion equipment affording between them restricted air leakage flow passages into the'combustion space, whereby the air leaking through said passages flows substantially over the whole of the surface of said second wall facing the combustion space.
  • Gas-turbine engine combustion equipment as claimed in claim 6, comprising holes in said other end flanges to place the spaces between the webs in communication with the exterior of said other end flanges, for the flow of cooling gas from the space immediately within the outer air casing structure to the combustion space.
  • Gas-turbine engine combustion equipment comprising a heat-resisting wall structure defining a combustion space which wall structure comprises at least one ring of material of H-section, the central web of the section extending radially and the two flanges of the section extending axially, one of said flanges of the ring or each ring being welded to adjacent annular portions of the wall structure so as effectively to form part of the wall structure, the web extending towards the combustion space from said one flange, and the other flange being slotted transversely to provide a multiplicity of pieces which are supported by the web, and air inlet holes being provided in the region of the wall structure adjacent said web for the passage of pressure cooling air from the exterior of the wall structure into the interior thereof.
  • Gas-turbine engine combustion equipment as claimed in claim 10 in which a plurality of rings of H-section material are provided adjacent one another with their corresponding flanges close together, the flanges remote from the combustion space being welded together.
  • Gas-turbine engine combustion equipment comprising an outer air casing structure which contains a flame tube made up of H-section strip which strip comprises a pair of end flanges interconnected by a web formation, the one end flange affording part at least of a first wall of the flame tube which defines a combustion space and the other end flange forming part at least of a continuous support wall on the side of the first wall remote from the combustion space, pressure cooling air being fed to the spaces between the walls, said one end flange being slotted transversely to provide a multiplicity of relatively small pieces arranged mosaicwise and having surfaces thereof facing the combustion space contained in a substantially continuous geometrical surface, the edges of adjacent pieces being unjoined but close to one another, and at least those edges of said pieces and adjacent parts of said first wall which extend in directions transversely to the general direction of gas flow through the combustion equipment affording between them restricted air leakage flow' passages into the combustion space, whereby the air leaking through said passages flows substantially over the whole of the surface of said second wall facing the combustion space.

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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)
  • Gasket Seals (AREA)
US484492A 1954-02-26 1955-01-27 Heat-resisting wall structures Expired - Lifetime US2919549A (en)

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GB331954X 1954-02-26
GB260155X 1955-01-26

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US (1) US2919549A (enrdf_load_stackoverflow)
BE (1) BE535497A (enrdf_load_stackoverflow)
CH (1) CH331954A (enrdf_load_stackoverflow)
DE (1) DE1052750B (enrdf_load_stackoverflow)
FR (1) FR1122030A (enrdf_load_stackoverflow)
GB (2) GB790293A (enrdf_load_stackoverflow)

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US3899876A (en) * 1968-11-15 1975-08-19 Secr Defence Brit Flame tube for a gas turbine combustion equipment
US3910036A (en) * 1974-04-05 1975-10-07 Gen Motors Corp Igniter installation for combustor with ceramic liner
US3943703A (en) * 1973-05-22 1976-03-16 United Turbine AB and Co., Kommanditbolag Cooling passages through resilient clamping members in a gas turbine power plant
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US4085580A (en) * 1975-11-29 1978-04-25 Rolls-Royce Limited Combustion chambers for gas turbine engines
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US4315406A (en) * 1979-05-01 1982-02-16 Rolls-Royce Limited Perforate laminated material and combustion chambers made therefrom
US4414816A (en) * 1980-04-02 1983-11-15 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Combustor liner construction
US4422300A (en) * 1981-12-14 1983-12-27 United Technologies Corporation Prestressed combustor liner for gas turbine engine
US4441324A (en) * 1980-04-02 1984-04-10 Kogyo Gijutsuin Thermal shield structure with ceramic wall surface exposed to high temperature
US4480436A (en) * 1972-12-19 1984-11-06 General Electric Company Combustion chamber construction
US4614082A (en) * 1972-12-19 1986-09-30 General Electric Company Combustion chamber construction
US4642993A (en) * 1985-04-29 1987-02-17 Avco Corporation Combustor liner wall
US4664618A (en) * 1984-08-16 1987-05-12 American Combustion, Inc. Recuperative furnace wall
US4695247A (en) * 1985-04-05 1987-09-22 Director-General Of The Agency Of Industrial Science & Technology Combustor of gas turbine
US4749029A (en) * 1985-12-02 1988-06-07 Kraftwerk Union Aktiengesellschaft Heat sheild assembly, especially for structural parts of gas turbine systems
US5113660A (en) * 1990-06-27 1992-05-19 The United States Of America As Represented By The Secretary Of The Air Force High temperature combustor liner
US5184455A (en) * 1991-07-09 1993-02-09 The United States Of America As Represented By The Secretary Of The Air Force Ceramic blanket augmentor liner
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US4422300A (en) * 1981-12-14 1983-12-27 United Technologies Corporation Prestressed combustor liner for gas turbine engine
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US4642993A (en) * 1985-04-29 1987-02-17 Avco Corporation Combustor liner wall
US4749029A (en) * 1985-12-02 1988-06-07 Kraftwerk Union Aktiengesellschaft Heat sheild assembly, especially for structural parts of gas turbine systems
US5639531A (en) * 1987-12-21 1997-06-17 United Technologies Corporation Process for making a hybrid ceramic article
US5113660A (en) * 1990-06-27 1992-05-19 The United States Of America As Represented By The Secretary Of The Air Force High temperature combustor liner
US5233798A (en) * 1991-03-06 1993-08-10 Shaw Clive A Enabling assembly
US5184455A (en) * 1991-07-09 1993-02-09 The United States Of America As Represented By The Secretary Of The Air Force Ceramic blanket augmentor liner
US5216886A (en) * 1991-08-14 1993-06-08 The United States Of America As Represented By The Secretary Of The Air Force Segmented cell wall liner for a combustion chamber
US5331816A (en) * 1992-10-13 1994-07-26 United Technologies Corporation Gas turbine engine combustor fiber reinforced glass ceramic matrix liner with embedded refractory ceramic tiles
US5605046A (en) * 1995-10-26 1997-02-25 Liang; George P. Cooled liner apparatus
EP0819842A1 (de) * 1996-07-15 1998-01-21 Siemens Aktiengesellschaft Vorrichtung zum Befestigen eines Abdeckbleches im Rauchgaskanal einer Gasturbine
US5758504A (en) * 1996-08-05 1998-06-02 Solar Turbines Incorporated Impingement/effusion cooled combustor liner
EP1006315A1 (de) * 1998-11-30 2000-06-07 Asea Brown Boveri AG Keramische Auskleidung für einen Brennraum
US6223538B1 (en) 1998-11-30 2001-05-01 Asea Brown Boveri Ag Ceramic lining
EP1208290A4 (en) * 1999-06-29 2003-10-15 Allison Advanced Dev Company I AILETTE COOL
EP1091092A3 (en) * 1999-10-05 2004-03-03 United Technologies Corporation Method and apparatus for cooling a wall within a gas turbine engine
US6408628B1 (en) * 1999-11-06 2002-06-25 Rolls-Royce Plc Wall elements for gas turbine engine combustors
EP1710501A3 (en) * 1999-11-06 2008-01-23 Rolls-Royce plc Wall elements for gas turbine engine combustors
EP1098141A1 (en) * 1999-11-06 2001-05-09 Rolls-Royce Plc Wall elements for gas turbine engine combustors
US6675586B2 (en) * 2001-06-27 2004-01-13 Siemens Aktiengesellschaft Heat shield arrangement for a component carrying hot gas, in particular for structural parts of gas turbines
RU2212587C2 (ru) * 2001-08-16 2003-09-20 Открытое акционерное общество "Научно-производственное объединение "Сатурн" Жаровая труба камеры сгорания газотурбинного двигателя
US6830437B2 (en) * 2002-12-13 2004-12-14 General Electric Company Assembly containing a composite article and assembly method therefor
US20040115395A1 (en) * 2002-12-13 2004-06-17 General Electric Company Assembly containing a composite article and assembly method therefor
US20100186365A1 (en) * 2003-10-27 2010-07-29 Holger Grote Heat Shield Element, in Particular for Lining a Combustion Chamber Wall
US8857190B2 (en) * 2003-10-27 2014-10-14 Siemens Aktiengesellschaft Heat shield element, in particular for lining a combustion chamber wall
US20070193216A1 (en) * 2006-01-25 2007-08-23 Woolford James R Wall elements for gas turbine engine combustors
US8650882B2 (en) * 2006-01-25 2014-02-18 Rolls-Royce Plc Wall elements for gas turbine engine combustors
EP2094964A4 (en) * 2006-12-19 2013-05-01 Volvo Aero Corp MOTOR-FUSE WALL
US20100162716A1 (en) * 2008-12-29 2010-07-01 Bastnagel Philip M Paneled combustion liner
US8453455B2 (en) * 2008-12-29 2013-06-04 Rolls-Royce Corporation Paneled combustion liner having nodes
US20100236250A1 (en) * 2009-03-23 2010-09-23 Paul Headland Combustion chamber brazed with ceramic inserts
EP2233835A1 (en) * 2009-03-23 2010-09-29 Siemens Aktiengesellschaft Combustion chamber brazed with ceramic inserts
US20110030378A1 (en) * 2009-08-05 2011-02-10 Rolls-Royce Plc Combustor tile mounting arrangement
US8833084B2 (en) * 2009-08-05 2014-09-16 Rolls-Royce Plc Combustor tile mounting arrangement
US9366143B2 (en) 2010-04-22 2016-06-14 Mikro Systems, Inc. Cooling module design and method for cooling components of a gas turbine system
US8959886B2 (en) * 2010-07-08 2015-02-24 Siemens Energy, Inc. Mesh cooled conduit for conveying combustion gases
US20120006518A1 (en) * 2010-07-08 2012-01-12 Ching-Pang Lee Mesh cooled conduit for conveying combustion gases
US20130327057A1 (en) * 2012-06-07 2013-12-12 United Technologies Corporation Combustor liner with improved film cooling
US9243801B2 (en) * 2012-06-07 2016-01-26 United Technologies Corporation Combustor liner with improved film cooling
EP2913588A1 (en) * 2014-02-27 2015-09-02 Rolls-Royce plc A combustion chamber wall and a method of manufacturing a combustion chamber wall
US10260749B2 (en) 2014-02-27 2019-04-16 Rolls-Royce Plc Combustion chamber wall and a method of manufacturing a combustion chamber wall
EP3242085A1 (en) * 2014-02-27 2017-11-08 Rolls-Royce plc A combustion chamber wall and a method of manufacturing a combustion chamber wall
US20160258624A1 (en) * 2015-02-04 2016-09-08 Rolls-Royce Plc Combustion chamber and a combustion chamber segment
US10502421B2 (en) * 2015-02-04 2019-12-10 Rolls-Royce Plc Combustion chamber and a combustion chamber segment
WO2017003458A1 (en) * 2015-06-30 2017-01-05 Siemens Energy, Inc. Hybrid component comprising a metal-reinforced ceramic matrix composite material
EP3130853A1 (en) * 2015-08-13 2017-02-15 Rolls-Royce plc A combustion chamber and a combustion chamber segment
US10634350B2 (en) 2015-08-13 2020-04-28 Rolls-Royce Plc Combustion chamber and a combustion chamber segment
US10577944B2 (en) * 2017-08-03 2020-03-03 General Electric Company Engine component with hollow turbulators
US11208899B2 (en) * 2018-03-14 2021-12-28 General Electric Company Cooling assembly for a turbine assembly
US10968750B2 (en) * 2018-09-04 2021-04-06 General Electric Company Component for a turbine engine with a hollow pin
US11377963B2 (en) 2018-09-04 2022-07-05 General Electric Company Component for a turbine engine with a conduit
US20220113028A1 (en) * 2020-10-09 2022-04-14 Pratt & Whitney Canada Corp. Combustor liner and method of operating same
US11506383B2 (en) * 2020-10-09 2022-11-22 Pratt & Whitney Canada Corp Combustor liner and method of operating same
US12313264B2 (en) 2022-10-20 2025-05-27 General Electric Company Coupling assembly for a turbine engine

Also Published As

Publication number Publication date
GB790293A (en) 1958-02-05
GB790292A (en) 1958-02-05
DE1052750B (de) 1959-03-12
CH331954A (de) 1958-08-15
BE535497A (enrdf_load_stackoverflow)
FR1122030A (fr) 1956-08-30

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