US2915877A - Cylindrical furnaces - Google Patents

Cylindrical furnaces Download PDF

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Publication number
US2915877A
US2915877A US486238A US48623855A US2915877A US 2915877 A US2915877 A US 2915877A US 486238 A US486238 A US 486238A US 48623855 A US48623855 A US 48623855A US 2915877 A US2915877 A US 2915877A
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United States
Prior art keywords
plates
bricks
longitudinal
circumferential direction
extent
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Expired - Lifetime
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US486238A
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Darling Robert Francis
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Parsons and Marine Engineering Turbine Research and Development Association
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Individual
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M5/00—Casings; Linings; Walls
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M5/00—Casings; Linings; Walls
    • F23M5/02—Casings; Linings; Walls characterised by the shape of the bricks or blocks used
    • 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

Definitions

  • This invention relates to cylindrical furnaces incorporating refractory bricks and has for its object to provide improved or simplified constructions thereof permitting substantial expansion and contraction on heating and cooling.
  • the invention is applicable particularly, though not exclusively, to flame tubes of gas turbine combustion chambers wherein air pressure on the exterior of the tubes exceeds the pressure within the tubes.
  • the invention consists in a cylindrical furnace having features as set forth in the claims appended hereto.
  • Figure l is a longitudinal section of one convenient construction embodying the present invention.
  • Figure 2 is a cross-sectional view partly on the line 11-11 and partly on the line IIaIIa of Figure 1.
  • Figure 3 is a full sized longitudinal sectionalview of one of the bricks on the line III--III of Figure 4.
  • Figure 4 is a cross-sectional view of one of the bricks on the line IVIV of Figure 3.
  • the interlocking is conveniently performed by the provision of ridges k and grooves m at the edges of each brick, these ridges and grooves being adapted to mate as shown in Figure 1 when the combustion chamber is erected.
  • Each set of bricks is carried in a metal channel plate b screwed at each end by bolts to an end metal ring d, the bricks being furnished with curved lips i which are adapted to be gripped by the channel plates.
  • the cross-section of the channel plates causes them to be rigid in the longitudinal direction but the metal is thin enough for them to be quite flexible in the circumferential direction.
  • the longitudinal edges b of the channel plates engage similarly shaped edges on the bricks and the latter also embody overhanging lips i for protecting the metal plates in the completed assembly.
  • the end rings are rigidly secured to each other conveniently by two or more bridge pieces e extending longitudinally and on the outside of the channel plates two or more cover plates 1 are provided which conveniently may be secured in position by the same tap bolts as those holding the channel plates.
  • These cover plates are furnished with perforations g in register with gaps h separating adjacent sets of bricks and channel plates so that air in passing inwards through the perforations and gaps effects cooling of these regions.
  • the tap bolts 0 are located some way in from the longitudinal edges of the channel plates to enable the United States Patent 0 "ice portions of these plates outboard of the tap bolt to be free to flex as the bricks expand and contract.
  • a refractory-lined cylinder is produced wherein the channel plates b are protected from the flame inside the cylinder by the overhanging lips i on the edges of the bricks. The edges of the channel plates are also protected by the flow of cooling air through the perforations g. Portions of the 'flame tube upstream and downstream of the refractorylined cylinder may conveniently be attached to the end rings, e.g. by means of further tap bolts.
  • a cylindrical combustion chamber at least two axially spaced fixed supporting rings, a series of longitudinally extending, circumferentially spaced plates secured to said rings, said plates having their opposite longitudinal edges turned inwards towards one another so as to define retaining channels, the cross section of said plates being such in relation to their longitudinal extent and their extent in the circumferential direction that the plates are stiff in the longitudinal direction but flexible in the circumferential direction, and refractory bricks having longitudinally extending grooves on opposite lateral sides thereof accommodated in said retaining channels.
  • said plates having such cross section in relation to their longitudinal extent and their extent in the circumferential direction as to be rigid in the longitudinal direction, but flexible in the circumferential direction, refractory bricks having longitudinally extending grooves on opposite sides thereof accommodated in said retaining channels and securing means connecting the portions of the plates extending beyond' the retaining channels to said rings.
  • a cylindrical combustion chamber at least two axially spaced fixed supporting rings, a series of longitudinally extending plates, securing means connecting said plates to said rings so that the plates are disposed in circumferentially spaced relationship, the opposite longitudinal edges of the plates being turned inwards toward one another so as to define retaining channels, the cross section of said plates in relation to their extent in the longitudinal direction and their extent in the circumferential direction being such that the plates are rigid in the longitudinal direction but flexible in the circumferential direction and said securing means being disposed inwards from the longitudinal edges of the plates so that those portions of the plates laterally outwards of the securing means are free to flex as the bricks expand and contract.
  • a cylindrical combustion chamber at least two axially spaced fixed supporting rings, a series of longitudinally extending, circumferentially spaced plates secured to said rings, said plates having their opposite longitudinal edges turned inwards toward one another so as to define retaining channels, the cross section of said plates being such in relation to their longitudinal extent and their extent in the circumferential direction that the plates are stiff in thelongitudinal direction but flexible in the circumferential direction, refractory bricks having longitudinally extending grooves on opposite lateral sides thereof accommodated in said retaining channels, cover plates extending over a plurality of said longitudinally extending plates and said cover plates being perforated at points in register with the longitudinally extending spaces between said first-mentioned plates so as to permit air to flow through said spaces, thus afiording further protection to the edges of the longitudinally extending plates to minimize the danger of overheating.

Description

R. F. DARLING CYLINDRICAL FURNACES Dec 8,
Filed Feb. 4, 1955 2 Sheets-Sheet l Dec. 8, 1959 R. F. DARLING CYLINDRICAL FURNACES 2 Sheets-Sheet 2 Filed Feb. 4, 1955 2,915,877 CYLINDRICAL FURNACES Robert Francis Darling, Monkseaton, England, assignor to The Parsons and Marine Engineering Turbine Research and Development Association, Wallsend, England This invention relates to cylindrical furnaces incorporating refractory bricks and has for its object to provide improved or simplified constructions thereof permitting substantial expansion and contraction on heating and cooling.
The invention is applicable particularly, though not exclusively, to flame tubes of gas turbine combustion chambers wherein air pressure on the exterior of the tubes exceeds the pressure within the tubes.
The invention consists in a cylindrical furnace having features as set forth in the claims appended hereto.
Referring to the accompanying diagrammatic drawings:
Figure l is a longitudinal section of one convenient construction embodying the present invention.
Figure 2 is a cross-sectional view partly on the line 11-11 and partly on the line IIaIIa of Figure 1.
Figure 3 is a full sized longitudinal sectionalview of one of the bricks on the line III--III of Figure 4.
Figure 4 is a cross-sectional view of one of the bricks on the line IVIV of Figure 3.
In carrying the invention into effect according to one form illustrated by way of example in the accompanying drawings as applied to the flame tube of a gas turbine combustion chamber wherein the air pressure on the outside of the cylinder is greater than that on the inside, six sets of refractory bricks are provided, each brick a being of segmental form and adapted to interlock with adjacent bricks.
The interlocking is conveniently performed by the provision of ridges k and grooves m at the edges of each brick, these ridges and grooves being adapted to mate as shown in Figure 1 when the combustion chamber is erected.
Each set of bricks is carried in a metal channel plate b screwed at each end by bolts to an end metal ring d, the bricks being furnished with curved lips i which are adapted to be gripped by the channel plates. The cross-section of the channel plates causes them to be rigid in the longitudinal direction but the metal is thin enough for them to be quite flexible in the circumferential direction. The longitudinal edges b of the channel plates engage similarly shaped edges on the bricks and the latter also embody overhanging lips i for protecting the metal plates in the completed assembly.
The end rings are rigidly secured to each other conveniently by two or more bridge pieces e extending longitudinally and on the outside of the channel plates two or more cover plates 1 are provided which conveniently may be secured in position by the same tap bolts as those holding the channel plates. These cover plates are furnished with perforations g in register with gaps h separating adjacent sets of bricks and channel plates so that air in passing inwards through the perforations and gaps effects cooling of these regions.
The tap bolts 0 are located some way in from the longitudinal edges of the channel plates to enable the United States Patent 0 "ice portions of these plates outboard of the tap bolt to be free to flex as the bricks expand and contract.
When the structure is erected, a refractory-lined cylinder is produced wherein the channel plates b are protected from the flame inside the cylinder by the overhanging lips i on the edges of the bricks. The edges of the channel plates are also protected by the flow of cooling air through the perforations g. Portions of the 'flame tube upstream and downstream of the refractorylined cylinder may conveniently be attached to the end rings, e.g. by means of further tap bolts.
What I claim is:
1. In a cylindrical combustion chamber, at least two axially spaced fixed supporting rings, a series of longitudinally extending, circumferentially spaced plates secured to said rings, said plates having their opposite longitudinal edges turned inwards towards one another so as to define retaining channels, the cross section of said plates being such in relation to their longitudinal extent and their extent in the circumferential direction that the plates are stiff in the longitudinal direction but flexible in the circumferential direction, and refractory bricks having longitudinally extending grooves on opposite lateral sides thereof accommodated in said retaining channels.
2. In a cylindrical combustion chamber, at least two axially spaced fixed supporting rings, a series of longitudinally extending, circumferentially spaced plates, the opposite longitudinal edges of said plates being turned inwards toward one another throughout the major extent of the plates so as to define retaining channels terminating short of the opposite longitudinal ends of the plates,
said plates having such cross section in relation to their longitudinal extent and their extent in the circumferential direction as to be rigid in the longitudinal direction, but flexible in the circumferential direction, refractory bricks having longitudinally extending grooves on opposite sides thereof accommodated in said retaining channels and securing means connecting the portions of the plates extending beyond' the retaining channels to said rings.
3. In a cylindrical combustion chamber, at least two axially spaced fixed supporting rings, a series of longitudinally extending plates, securing means connecting said plates to said rings so that the plates are disposed in circumferentially spaced relationship, the opposite longitudinal edges of the plates being turned inwards toward one another so as to define retaining channels, the cross section of said plates in relation to their extent in the longitudinal direction and their extent in the circumferential direction being such that the plates are rigid in the longitudinal direction but flexible in the circumferential direction and said securing means being disposed inwards from the longitudinal edges of the plates so that those portions of the plates laterally outwards of the securing means are free to flex as the bricks expand and contract.
4. In a cylindrical combustion chamber, at least two axially spaced fixed supporting rings, a series of longitudinally extending, circumferentially spaced plates secured to said rings, said plates having their opposite longitudinal edges turned inwards toward one another so as to define retaining channels, the cross section of said plates being such in relation to their longitudinal extent and their extent in the circumferential direction that the plates are stiff in thelongitudinal direction but flexible in the circumferential direction, refractory bricks having longitudinally extending grooves on opposite lateral sides thereof accommodated in said retaining channels, cover plates extending over a plurality of said longitudinally extending plates and said cover plates being perforated at points in register with the longitudinally extending spaces between said first-mentioned plates so as to permit air to flow through said spaces, thus afiording further protection to the edges of the longitudinally extending plates to minimize the danger of overheating. 5. In a cylindrical combustion chamber, at least two axially spaced fixed supporting rings, a series of longitudin'ally extending, circumferentially spaced plates seeured' to said rings, said plates having their opposite longitudinal edges turned inwards toward one another so as to define retaining channels, the vcross section of said plates being such in relation to their longitudinal extent and their extent in the circumferential direction that the .plates are stiff in the longitudinal direction but flexible in the circumferential direction, refractory bricks having References Cited in the file of this patent UNITED STATES PATENTS v Thompson Feb. 1, 1881 2,548,485 Lubbock Apr. 10, 1951 2,617,255
Niehus Nov. 11, 1952
US486238A 1954-03-03 1955-02-04 Cylindrical furnaces Expired - Lifetime US2915877A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB6208/54A GB758213A (en) 1954-03-03 1954-03-03 Improvements in and relating to cylindrical combustion chambers or furnaces

Publications (1)

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US2915877A true US2915877A (en) 1959-12-08

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US486238A Expired - Lifetime US2915877A (en) 1954-03-03 1955-02-04 Cylindrical furnaces

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CH (1) CH330271A (en)
DE (1) DE1021647B (en)
FR (1) FR1119125A (en)
GB (1) GB758213A (en)

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3380409A (en) * 1966-06-13 1968-04-30 Dresser Ind Air-cooled wall construction for incinerators
USB377172I5 (en) * 1973-07-06 1975-01-28
US3939783A (en) * 1973-09-28 1976-02-24 B. V. Peximac Furnace for incinerating waste materials
US3956886A (en) * 1973-12-07 1976-05-18 Joseph Lucas (Industries) Limited Flame tubes for gas turbine engines
US4441324A (en) * 1980-04-02 1984-04-10 Kogyo Gijutsuin Thermal shield structure with ceramic wall surface exposed to high temperature
US4596116A (en) * 1983-02-10 1986-06-24 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Sealing ring for a turbine rotor of a turbo machine and turbo machine installations provided with such rings
US5375420A (en) * 1992-03-30 1994-12-27 General Electric Company Segmented centerbody for a double annular combustor
US5431020A (en) * 1990-11-29 1995-07-11 Siemens Aktiengesellschaft Ceramic heat shield on a load-bearing structure
FR2726072A1 (en) * 1994-10-21 1996-04-26 Gen Electric DOUBLE COMBUSTION CHAMBER FOR TURBOMOTOR
US6286338B2 (en) * 1998-02-26 2001-09-11 Visteon Global Technologies, Inc. Block assembly for a gas-type lehr
US20030056515A1 (en) * 2001-08-28 2003-03-27 Ulrich Bast Heat shield block and use of a heat shield block in a cobustion chamber
US20030079475A1 (en) * 2001-10-15 2003-05-01 Milan Schmahl Lining for inner walls of combustion chambers
WO2006089496A1 (en) * 2005-02-24 2006-08-31 Diz Bohemia S.R.O Connecting mouth for a combustion burner
CN103518100A (en) * 2011-05-12 2014-01-15 西门子公司 Heat shield assembly
WO2017003458A1 (en) * 2015-06-30 2017-01-05 Siemens Energy, Inc. Hybrid component comprising a metal-reinforced ceramic matrix composite material
US20180340687A1 (en) * 2017-05-24 2018-11-29 Siemens Aktiengesellschaft Refractory ceramic component for a gas turbine engine

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2211285A (en) * 1987-10-20 1989-06-28 Rolls Royce Plc Combustion equipment
DE59005482D1 (en) * 1990-07-17 1994-05-26 Siemens Ag Pipe piece, in particular flame tube, with a cooled support frame for a heat-resistant lining.
DE9219073U1 (en) * 1991-02-13 1997-08-28 Lampka Bruno Shaped stone
FR2685035B1 (en) * 1991-12-16 1994-03-25 Aerospatiale DEVICE FOR MOUNTING TWO PARTS OF MATERIALS WITH DIFFERENT COEFFICIENTS, SUBJECT TO HIGH TEMPERATURE VARIATIONS.
US5636508A (en) * 1994-10-07 1997-06-10 Solar Turbines Incorporated Wedge edge ceramic combustor tile
DE19813897A1 (en) * 1998-03-28 1999-09-30 Bosch Gmbh Robert Segmented insulation for burners with porous media
EP1128131A1 (en) * 2000-02-23 2001-08-29 Siemens Aktiengesellschaft Heat shield element, combustion chamber and gas turbine

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US237339A (en) * 1881-02-01 Sectional furnace
US2548485A (en) * 1946-01-09 1951-04-10 Shell Dev Combustion chamber lining
US2617255A (en) * 1947-05-12 1952-11-11 Bbc Brown Boveri & Cie Combustion chamber for a gas turbine

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2530019A (en) * 1944-11-11 1950-11-14 Elliott Co Combustion chamber with side air entrance and hollow ignition cone

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US237339A (en) * 1881-02-01 Sectional furnace
US2548485A (en) * 1946-01-09 1951-04-10 Shell Dev Combustion chamber lining
US2617255A (en) * 1947-05-12 1952-11-11 Bbc Brown Boveri & Cie Combustion chamber for a gas turbine

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3380409A (en) * 1966-06-13 1968-04-30 Dresser Ind Air-cooled wall construction for incinerators
USB377172I5 (en) * 1973-07-06 1975-01-28
US3918255A (en) * 1973-07-06 1975-11-11 Westinghouse Electric Corp Ceramic-lined combustion chamber and means for support of a liner with combustion air penetrations
US3939783A (en) * 1973-09-28 1976-02-24 B. V. Peximac Furnace for incinerating waste materials
US3956886A (en) * 1973-12-07 1976-05-18 Joseph Lucas (Industries) Limited Flame tubes for gas turbine engines
US4441324A (en) * 1980-04-02 1984-04-10 Kogyo Gijutsuin Thermal shield structure with ceramic wall surface exposed to high temperature
US4596116A (en) * 1983-02-10 1986-06-24 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Sealing ring for a turbine rotor of a turbo machine and turbo machine installations provided with such rings
US5431020A (en) * 1990-11-29 1995-07-11 Siemens Aktiengesellschaft Ceramic heat shield on a load-bearing structure
US5375420A (en) * 1992-03-30 1994-12-27 General Electric Company Segmented centerbody for a double annular combustor
FR2726072A1 (en) * 1994-10-21 1996-04-26 Gen Electric DOUBLE COMBUSTION CHAMBER FOR TURBOMOTOR
US6286338B2 (en) * 1998-02-26 2001-09-11 Visteon Global Technologies, Inc. Block assembly for a gas-type lehr
US20030056515A1 (en) * 2001-08-28 2003-03-27 Ulrich Bast Heat shield block and use of a heat shield block in a cobustion chamber
US6711899B2 (en) * 2001-08-28 2004-03-30 Siemens Aktiengesellschaft Heat shield block and use of a heat shield block in a combustion chamber
US20030079475A1 (en) * 2001-10-15 2003-05-01 Milan Schmahl Lining for inner walls of combustion chambers
US6840047B2 (en) * 2001-10-15 2005-01-11 Siemens Aktiengesellschaft Lining for inner walls of combustion chambers
WO2006089496A1 (en) * 2005-02-24 2006-08-31 Diz Bohemia S.R.O Connecting mouth for a combustion burner
CN103518100A (en) * 2011-05-12 2014-01-15 西门子公司 Heat shield assembly
WO2017003458A1 (en) * 2015-06-30 2017-01-05 Siemens Energy, Inc. Hybrid component comprising a metal-reinforced ceramic matrix composite material
US20180292090A1 (en) * 2015-06-30 2018-10-11 Siemens Energy, Inc. Hybrid component comprising a metal-reinforced ceramic matrix composite material
US20180340687A1 (en) * 2017-05-24 2018-11-29 Siemens Aktiengesellschaft Refractory ceramic component for a gas turbine engine

Also Published As

Publication number Publication date
FR1119125A (en) 1956-06-15
CH330271A (en) 1958-05-31
DE1021647B (en) 1957-12-27
GB758213A (en) 1956-10-03

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