US2544538A - Liner for hot gas chambers - Google Patents
Liner for hot gas chambers Download PDFInfo
- Publication number
- US2544538A US2544538A US62924A US6292448A US2544538A US 2544538 A US2544538 A US 2544538A US 62924 A US62924 A US 62924A US 6292448 A US6292448 A US 6292448A US 2544538 A US2544538 A US 2544538A
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- Prior art keywords
- strips
- wall
- liner
- chamber
- adjacent
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- 238000010276 construction Methods 0.000 description 33
- 239000002184 metal Substances 0.000 description 26
- 239000007789 gas Substances 0.000 description 19
- 230000008602 contraction Effects 0.000 description 8
- 239000012530 fluid Substances 0.000 description 6
- 238000002485 combustion reaction Methods 0.000 description 4
- 238000001816 cooling Methods 0.000 description 2
- 239000012809 cooling fluid Substances 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000011810 insulating material Substances 0.000 description 1
Images
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
- 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
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- 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
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S220/00—Receptacles
- Y10S220/917—Corrosion resistant container
Definitions
- This invention relates to combustion or other hot gas chambers'and/or ducts and is particularly directed to an internal liner construction Therefore not only should the chamber liner construction be such so as not to buckle or warp upon a uniform increase-in temperature within said chamber but said liner construction should not buckle or warp even though the increase in temperature is non-uniform. Accordingly an object of this invention comprises the provision of a novel and simple liner construction for a hot gas chamber which does not buckle or warp with changes in temperature in' said chamber regardless of whether said changes are uniform or nonuniform throughout said chamber.
- Figure 1 is a perspective view partly in section illustrating a combustion or other hot gas chamber having a liner construction embodying the invention
- Figure 2 is an enlarged view ofa portion of Figure 1 with some of the liners removed;
- Figure 3 is an enlarged sectional view taken along line 3-4 of Figure 1.
- reference numeral I 0 designates the structurally rigid tube-like outer wall lo of a combustion or other hot gas chamber through which said gases flow.
- ' wall I0 is internally lined with a plurality of sideby-side elongate sheet metal strips l2 .and I4 preferably of heat and corrosion resistant stainwall It] and extending in the general direction of gas flow through said chamber.
- the strips i2 and it In a chamber having an outer wall 10 with a diameter of approximately flfty inches, the strips i2 and it have a width which is preferably no greater than side'wall of said channel member.
- metal strips 12 are parallel so thatsaid strips have a constant width while the strips ll taper in width, said strips I2 and It being otherwise similar.
- the reason for this difference in the shape of the sheet metal strips l2 and i4 is hereinafter explained.
- the sheet metal liner strips l2 and il are disposed so as to leave a gap l6 between the longitudinal edge of one strip and the adjacent longitudinal edge of the adjacent strip.
- Each strip l2 and It has a flange. l8 extending outwardly toward the adjacent portion of the chamber wall ill with the end of said flange bein turned toward a corresponding flange l8 formed along the other longitudinal edge of its strip.
- each channel member 20 is secured to the wall Ill by means hereinafter described.
- the bottom wall 22 of each channel member 20 faces the adjacent portion of the wall I0.
- the open end of each channel member 20 is. disposed parallelto, faces and bridges the gap li-formed between the adjacent longitudinal edges of a pair of sheet metal liner strips.
- the longitudinal edge of each side wall 24 of a channel member 20 is provided with a flange'ZB coextensive with said edge and extending toward a corresponding flange 26 formed along the other
- Each flange 26 of the channel members 20 is slidingly restrip overlying the channel side wall 24 of said flange 2B.
- each flange l8 forms a groove with its associated sheet metal strip within which the flange or tongue 26 of a channel member 20 is received.
- Each channel member 20 is supported on the interior surface of the wall III by a plurality of brackets 30.
- Each bracket 30 comprises a blade portion 32 with a flange 34 at its radially outer end and a flange 36 at its radially inner end.
- the flanges 34 and 36 are respectively secured to the chamber wall In and to the bottom wall 22 of its associated channel member 20, for example by welding.
- Each blade 32 is flat and is disposed in a plane at right angles to the longitudinal dimension of its associated channel member whereby said blade can bend or deflect in a direction parallel to said longitudinal dimension. This arrangement permits longitudinal expansion and contraction of the channel members 20 relative to the chamber wall Ill.
- a tapered strip I4 is first disposed slightly to the right ( Figure 1) of its ultimate position on the channel members so that each of its flanges It can be inserted laterally outwardly between the side flanges of a channel member 20. Said tapered strip I4 is then slid longitudinally to the left ( Figure 1) to its ultimate position so that its flanges l8 engage under the channel flanges 26.
- the rectangular strips l2 can be disposed in position on said channel members by simply longitudinally sliding said strips l2 into position between said tapered strips I.
- the invention obviously is not limited to a construction where alternate strips are tapered and the remaining strips are rectangular. If a pair of adjacent strips are both tapered the one strip should be longitudinally shifted to the left from its position of Figure 1 so as to permit each of the flanges l8 of the adjacent strip to be inserted laterally between the side walls 24 of a channel member 20.
- the chamber a large fluid pressure diflerence should occur between the pressure within said annular space and that within the chamber the liner strips l2 and I4 might buckle under said pressure difference.
- Some combustion or hot gas chambers-as for example the combustion chambers of gas turbine engines are subject to sudden large changes in pressure so that the leakage flow path between said annular space and the interior of the chamber should be sufficiently large to prevent the creation of large pressure differences across the liner strips l2 and. It as the result of said sudden pressure changes. Accordingly, it may be desirable to provide one or more holes 38 in at least some of the side walls 24 of the channel members 20, as illustrated in Figure 3, in order to decrease the resistance of said leakage flow path.
- each strip may be made slightly longer than its associated channel member 20 and then after said strips are assembled in position their projecting ends can be bent outwardly over the adjacent ends of the channel members 20, as indicated at 40 in Figure 2.
- the strip l2 and I4 form an internal liner construction or wall spaced from the outer chamber wall I0.
- cooling air or other fluid may be caused to flow through the annular space between said liner construction and the outer wall It.
- the quantity of cooling air flowing between said liner construction and the outer chamber wall I0 can be limited by the extent to formed by the wall I had a constant cross-sectional area then all the liner strips could be rectangular like the strips l2.
- the channel members 20 may.
- each liner strip may have a curvature in a plane parallel to its long dimension, as may be desired if the chamber wall III were provided with a similar longitudinal curvature. If each liner strip is provided with such a longitudinal curvature, then the channel supporting members 20 should be similarly curved.
- each tab 40 close oil the ends of the space between each liner strip I2 or H and the adjacent portion of the wall It; For example. if a large flow of cooling fluid is desired, each tab 40 may have large cut out opening or may be limited to two portions each disposed at a longitudinal edge of its liner strip and bent over the end.
- the annular space between the linerstrips I2 and I4 and the chamber wall l0 could be fllled with suitable heat insulating material.
- the flanges l8 of the sheet metal strips l2 and I 4 frictionally clamp the longitudinal edges of the respective strips to the flanges 26 of th channel members 20 so as to leave each sheet metal strip free to expand and contract in all directions along its surface relative to its supporting channel member 20.
- expansion and contraction of one sheet metal strip has no effect on its adjacent strip.
- the strips I2 and I4 are narrow in transverse width a local hot zone in any one of said strips will extend entirely across said strip and therefore will only cause longitudinal expansion of said strip.
- each liner strip I 2 or ll can readily be replaced without removing any of the other strips for example in case certain liners should become burned, mutilated, or otherwise damaged.
- a liner construction for a wall of a chamber the interiorof which is to be subjected to hot gases comprising a pinrality of elongate strips of sheet metal forming an internal liner for said wall, said strips being disposed in side-by-side relation with a gap between the adjacent longitudinal edges of each pair of adjacent strips; and means for supporting saidstrips from said wall so as to permit expansion and contraction of each strip in all directions along its surface relative to the adjae cent strips.
- a liner construction as recited in claim 1 her the interior of which is to be subjected to hot gases; said construction comprising a, plurality of elongate strips of sheet metal forming an internal liner for said wall, said strips being disposed in side-by-side relation with a gap between the adjacent longitudinal edges of each pair of adjacent strips, each of said elongate strips having a flange along its one longitudinal edge turned toward a corresponding flange along its other longitudinal edge; and means secured to said wall and only frictionally' engaged by said flanges for supporting said elongate strips.
- a liner construction for a wall of a chamber the interior of which is to be subjected to hot gases comprising a plurality of elongate strips of sheet metal forming an internal liner for said wall, said strips being disposed in side-by-side relation with. a gap between the adjacent longitudinal edges of each pair of adjacent strips; and a plurality of elongate members secured to'said wall for supporting said strips, each of said support members being disposed parallel to a longitudinal edge of one of said strips and having a longitudinal flange overlying a surface of said longitudinal edge facing the interior of said chamber.
- a liner construction for at least a portion of a tube-like wall of a chamber the interior of which is to' be subjected to hot gases flowing therethrough; said construction comprising a plurality of elongate strips of sheet metal extending in the general direction of new through said chamber and forming an internal liner for said wall portion, said strips being disposed in side-by-side relation with a gap between the adjacent longitudinal edges of each pair of adjacent strips; and means secured to said wall portion and having a tongue and groove connection with the longitudinal edges 'of' said strips to support,
- a liner construction for at least a portion of a tube-like wall of a chamber the interior of which is to be subjected to hot gases flowing therethrough; said construction comprising a plurality of elongate strips of sheet metal extending in the general direction of flow through said chamber and forming an, internal liner for said chamber wall portion, said strips being disposed in side-by-side relation with a gap between the adjacent longitudinal edges of each pair or adjacent strips; a plurality of .elongate members disposed parallel to the longitudinal edges of said strips, means securing said elongate members to said chamber wall portion so as to permit their longitudinal expansion and contraction relative to said .wall portion, each longitudinal edge of said sheet metal strips having a tongue and groove connection with one of said elongate members for support thereby.
- a liner construction for a wall of achamber the interior of which is to be subjected to hot gases comprising a plurality of elongate stripsof sheet-metal forming an internal liner for said wall, said strips being disposed in side-by-side relation with a gap between the adjacent longitudinal edges of each pair of adjacent strips.
- each of said elongate strips having a flange along one longitudinal edge therethrough; said construction comprising a said strips so as to permit expansion and contraction of each stripin all directions along it surface relative to adjacent strips.
- a liner construction for at least a portion of a tube-like wall of a chamber the interior of which is to be subjected to hot gases flowing therethrough; said construction comprising a plurality of elongate strips of-sheet metal ex-' plurality of elongate strips of sheet metal extending in the general direction of flow through said chamber and forming an internal liner for said chamber wall portion, said strips being disposed in side-by-side relation with a gap between the adjacent longitudinal edges of each pair of adjacent strips, some of said strips having a constant width and other of said strips, disposed between said constant width strips.
- a liner construction for at least a portion of a tube-like wall of a chamber the interior of which is to be subjected to hot gases flowing therethrough; said construction comprising a plurality of elongate strips of sheet metal extending in the general direction of flow through said chamber and forming an internal liner for said wall portion, said strips being disposed in side-by-side relation with a gap between the adjacent longitudinal edges of each pair of adjacent strips, each of said elongate strips having a flange along one longitudinal edge turned toward 1 a corresponding flange along its other longitudi- 7 nal edge and each of said flanges being on the side of its strip facing said wall portion, and a plurality of channel members carried by said wall portion for supporting said elongate strips, each of said channel members having its bottom side facing said wall portion with its open side disposed parallel to, facing and bridging the gap between an adjacent pair of said elongate strips, each of said channel members also having a flange along one of its longitudinal edges extend ing toward
- a liner construction for at least a portion of a tube-like wall of a chamber the interior of which is to be subjected to hot gases flowing therethrough; said construction comprising a plurality of elongate strips of sheet metal extending in the general direction of flow through said chamber and forming an internal liner for said wall portion, said strips being disposed in side-by-side relation with a gap between the adjacent longitudinal edges of each pair of adjacent strips, each of said elongate strips having a flange along one longitudinal edge turned toward a corresponding flange along its other longitudinal edge and each of said flanges being on the side of its strip facing said wall portion, a plurality of channel members having its bottom side facing said channel members.
- each bracket member for supporting each channel member from said wall, each bracket member be-' ing secured at one end to said wall and its other end to one of said channel members and being capable of deflecting in a direction parallel to the longitudinal dimension of its channel member to permit longitudinal expansion and contraction of said channel member.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Description
March 6, 1951 W. W. MAHNKEN EI'AL LINER FOR HOT GAS CHAMBERS Filed Dec. 1, 1948 INVENTORS WALTER MI. MAHNKEN ROBERT ZEEEA.
ATTC) RN E'Y Patented Mar. 6, 1951 UNITED STATES PATENT orries LINER FOR no'r'cas CHAMBERS wauer vv. Malinken, Union- City, N. 1., and Robert Zecca. Brooklyn, N. Y., assignors to Wright Aeronautical Corporation, acorporation of New York Application December 1, 1948, Qerial No. 62,924
' 13 Claims.
This invention relates to combustion or other hot gas chambers'and/or ducts and is particularly directed to an internal liner construction Therefore not only should the chamber liner construction be such so as not to buckle or warp upon a uniform increase-in temperature within said chamber but said liner construction should not buckle or warp even though the increase in temperature is non-uniform. Accordingly an object of this invention comprises the provision of a novel and simple liner construction for a hot gas chamber which does not buckle or warp with changes in temperature in' said chamber regardless of whether said changes are uniform or nonuniform throughout said chamber.
Other objects of the invention will become apparent upon reading the annexed detailed description in connection with the drawing in which: t
Figure 1 is a perspective view partly in section illustrating a combustion or other hot gas chamber having a liner construction embodying the invention;
Figure 2 is an enlarged view ofa portion of Figure 1 with some of the liners removed; and
Figure 3 is an enlarged sectional view taken along line 3-4 of Figure 1.
Referring to the drawing, reference numeral I 0 designates the structurally rigid tube-like outer wall lo of a combustion or other hot gas chamber through which said gases flow. The
' wall I0 is internally lined with a plurality of sideby-side elongate sheet metal strips l2 .and I4 preferably of heat and corrosion resistant stainwall It] and extending in the general direction of gas flow through said chamber. In a chamber having an outer wall 10 with a diameter of approximately flfty inches, the strips i2 and it have a width which is preferably no greater than side'wall of said channel member.
The sheet metal liner strips l2 and il are disposed so as to leave a gap l6 between the longitudinal edge of one strip and the adjacent longitudinal edge of the adjacent strip. Each strip l2 and It has a flange. l8 extending outwardly toward the adjacent portion of the chamber wall ill with the end of said flange bein turned toward a corresponding flange l8 formed along the other longitudinal edge of its strip.
The sheet metal strips l2 and M are supported in spaced side-by-side relation by a. plurality of longitudinally extending channel members 20 secured to the wall Ill by means hereinafter described. The bottom wall 22 of each channel member 20 faces the adjacent portion of the wall I0. The open end of each channel member 20 is. disposed parallelto, faces and bridges the gap li-formed between the adjacent longitudinal edges of a pair of sheet metal liner strips. The longitudinal edge of each side wall 24 of a channel member 20 is provided with a flange'ZB coextensive with said edge and extending toward a corresponding flange 26 formed along the other Each flange 26 of the channel members 20 is slidingly restrip overlying the channel side wall 24 of said flange 2B. Thus each flange l8 forms a groove with its associated sheet metal strip within which the flange or tongue 26 of a channel member 20 is received.
Each channel member 20 is supported on the interior surface of the wall III by a plurality of brackets 30. Each bracket 30 comprises a blade portion 32 with a flange 34 at its radially outer end and a flange 36 at its radially inner end. The flanges 34 and 36 are respectively secured to the chamber wall In and to the bottom wall 22 of its associated channel member 20, for example by welding. Each blade 32 is flat and is disposed in a plane at right angles to the longitudinal dimension of its associated channel member whereby said blade can bend or deflect in a direction parallel to said longitudinal dimension. This arrangement permits longitudinal expansion and contraction of the channel members 20 relative to the chamber wall Ill.
three inches. The longitudinal edges of the As illustrated, the chamber wall It is conical,
construction, after the channel members 20 are secured to the wall ID, the tapered strips ll are assembled on the channel members 20 before the rectangular or constant width strips I! are assembled thereon. Thus a tapered strip I4 is first disposed slightly to the right (Figure 1) of its ultimate position on the channel members so that each of its flanges It can be inserted laterally outwardly between the side flanges of a channel member 20. Said tapered strip I4 is then slid longitudinally to the left (Figure 1) to its ultimate position so that its flanges l8 engage under the channel flanges 26. After all the tapered strips ll have been so disposed in position on the channel members 20, the rectangular strips l2 can be disposed in position on said channel members by simply longitudinally sliding said strips l2 into position between said tapered strips I. The invention obviously is not limited to a construction where alternate strips are tapered and the remaining strips are rectangular. If a pair of adjacent strips are both tapered the one strip should be longitudinally shifted to the left from its position of Figure 1 so as to permit each of the flanges l8 of the adjacent strip to be inserted laterally between the side walls 24 of a channel member 20. Obviously, if instead of being tapered the chamber a large fluid pressure diflerence should occur between the pressure within said annular space and that within the chamber the liner strips l2 and I4 might buckle under said pressure difference. Some combustion or hot gas chambers-as for example the combustion chambers of gas turbine enginesare subject to sudden large changes in pressure so that the leakage flow path between said annular space and the interior of the chamber should be sufficiently large to prevent the creation of large pressure differences across the liner strips l2 and. It as the result of said sudden pressure changes. Accordingly, it may be desirable to provide one or more holes 38 in at least some of the side walls 24 of the channel members 20, as illustrated in Figure 3, in order to decrease the resistance of said leakage flow path.
In order to prevent the sheet metal strips l2 and H from sliding longitudinally out of position, each strip may be made slightly longer than its associated channel member 20 and then after said strips are assembled in position their projecting ends can be bent outwardly over the adjacent ends of the channel members 20, as indicated at 40 in Figure 2.
The strip l2 and I4 form an internal liner construction or wall spaced from the outer chamber wall I0. Accord ng y, cooling air or other fluid may be caused to flow through the annular space between said liner construction and the outer wall It. The quantity of cooling air flowing between said liner construction and the outer chamber wall I0 can be limited by the extent to formed by the wall I had a constant cross-sectional area then all the liner strips could be rectangular like the strips l2.
It is not necessary to first secure the brackets and the channel members 20 to the chamber wall In before disposing the sheet metal liner strips l2 and 14 in position of said channel members. For example, the channel members 20 may.
be laid out on a flat surface withthe liner strips l2 and Il engaging the channel member flanges 26. This liner construction comprising the liner strips [2 and I4 and the channel members 20 is then handled asa unit and disposed in position within the chamber wall III on the brackets 30. The liners l2 and M are then temporarily slid longitudinally out of the way in order to permit welding of the channel members 20 to their supporting brackets 30. As already mentioned, the chamber wall I0 is conical and each liner strip l2 and I4 is flat. Obviously, however, as far as this invention is concerned said chamber need not be conical and each liner strip may have a transverse curvature corresponding to the circular transverse curvature of the chamber wall l0. Furthermore, each liner strip may have a curvature in a plane parallel to its long dimension, as may be desired if the chamber wall III were provided with a similar longitudinal curvature. If each liner strip is provided with such a longitudinal curvature, then the channel supporting members 20 should be similarly curved. v
The fit or junction between the flanges 26 and I 8 is only frictional, therefore fluid can flow or leak through said junction. Accordingly the fluid pressure within the chamber and the fluid pressure within the annular space between the liner strips l2 and I4 and the wall lfl'can equalize by fluid flow through the junction between the flanges 26 and Hi. This is important because if which the tabs 40 close oil the ends of the space between each liner strip I2 or H and the adjacent portion of the wall It; For example. if a large flow of cooling fluid is desired, each tab 40 may have large cut out opening or may be limited to two portions each disposed at a longitudinal edge of its liner strip and bent over the end.
of the adjacent channel member 20. In lieu of said cooling fluid flow, the annular space between the linerstrips I2 and I4 and the chamber wall l0 could be fllled with suitable heat insulating material.
With the aioredescribed construction, the flanges l8 of the sheet metal strips l2 and I 4 frictionally clamp the longitudinal edges of the respective strips to the flanges 26 of th channel members 20 so as to leave each sheet metal strip free to expand and contract in all directions along its surface relative to its supporting channel member 20. In addition, because of the gap l6 between said sheet metal strips, expansion and contraction of one sheet metal strip has no effect on its adjacent strip. Also because the strips I2 and I4 are narrow in transverse width a local hot zone in any one of said strips will extend entirely across said strip and therefore will only cause longitudinal expansion of said strip. Accordingly, the sheet metal liner construction for the wall l0 provided by the strips I2 and M will not buckle or warp because of high temperatures within the chamber formed by the wall In regardless of whether said temperature is uniform or non-uniform throughout said chamber. Another advantage of'the presentjconstruction. is that each liner strip I 2 or ll can readily be replaced without removing any of the other strips for example in case certain liners should become burned, mutilated, or otherwise damaged.
While we have described our invention in detail in its present preferred embodiment. it will be obvious to those skilled in the art, after understanding our invention, that various changes and modifications may be made therein without departing from the spirit or scope thereof. We aim inv the appended claims to modifications.
We claim as our invention:
1. A liner construction for a wall of a chamber the interiorof which is to be subjected to hot gases; said construction comprising a pinrality of elongate strips of sheet metal forming an internal liner for said wall, said strips being disposed in side-by-side relation with a gap between the adjacent longitudinal edges of each pair of adjacent strips; and means for supporting saidstrips from said wall so as to permit expansion and contraction of each strip in all directions along its surface relative to the adjae cent strips. r
2. A liner construction as recited in claim 1 her the interior of which is to be subjected to hot gases; said construction comprising a, plurality of elongate strips of sheet metal forming an internal liner for said wall, said strips being disposed in side-by-side relation with a gap between the adjacent longitudinal edges of each pair of adjacent strips, each of said elongate strips having a flange along its one longitudinal edge turned toward a corresponding flange along its other longitudinal edge; and means secured to said wall and only frictionally' engaged by said flanges for supporting said elongate strips.
4. A liner construction for a wall of a chamber the interior of which is to be subjected to hot gases; said'construction comprising a plurality of elongate strips of sheet metal forming an internal liner for said wall, said strips being disposed in side-by-side relation with. a gap between the adjacent longitudinal edges of each pair of adjacent strips; and a plurality of elongate members secured to'said wall for supporting said strips, each of said support members being disposed parallel to a longitudinal edge of one of said strips and having a longitudinal flange overlying a surface of said longitudinal edge facing the interior of said chamber.
5. A liner construction for at least a portion of a tube-like wall of a chamber the interior of which is to' be subjected to hot gases flowing therethrough; said construction comprising a plurality of elongate strips of sheet metal extending in the general direction of new through said chamber and forming an internal liner for said wall portion, said strips being disposed in side-by-side relation with a gap between the adjacent longitudinal edges of each pair of adjacent strips; and means secured to said wall portion and having a tongue and groove connection with the longitudinal edges 'of' said strips to support,
cover all "such 'bers disposed parallel to the longitudinal edges tion with one of said elongatemembers for sup- 7 port thereby.
'7. A liner construction for at least a portion of a tube-like wall of a chamber the interior of which is to be subjected to hot gases flowing therethrough; said construction comprising a plurality of elongate strips of sheet metal extending in the general direction of flow through said chamber and forming an, internal liner for said chamber wall portion, said strips being disposed in side-by-side relation with a gap between the adjacent longitudinal edges of each pair or adjacent strips; a plurality of .elongate members disposed parallel to the longitudinal edges of said strips, means securing said elongate members to said chamber wall portion so as to permit their longitudinal expansion and contraction relative to said .wall portion, each longitudinal edge of said sheet metal strips having a tongue and groove connection with one of said elongate members for support thereby.
8. A liner construction for a wall of achamber the interior of which is to be subjected to hot gases; said construction comprising a plurality of elongate stripsof sheet-metal forming an internal liner for said wall, said strips being disposed in side-by-side relation with a gap between the adjacent longitudinal edges of each pair of adjacent strips. each of said elongate strips having a flange along one longitudinal edge therethrough; said construction comprising a said strips so as to permit expansion and contraction of each stripin all directions along it surface relative to adjacent strips. L
6. A liner construction for at least a portion of a tube-like wall of a chamber the interior of which is to be subjected to hot gases flowing therethrough; said construction comprising a plurality of elongate strips of-sheet metal ex-' plurality of elongate strips of sheet metal extending in the general direction of flow through said chamber and forming an internal liner for said chamber wall portion, said strips being disposed in side-by-side relation with a gap between the adjacent longitudinal edges of each pair of adjacent strips, some of said strips having a constant width and other of said strips, disposed between said constant width strips. having a tapering width so that said strips provide a liner construction which has a taper conforming approximately to the taper of said wall, and means secured to said wall and having a tongue and groove connection with the longitudinal edges 01' said strips to support said strips from said wall so as to permit expansion and contraction of each strip in all directions along its surface, relative to adjacent strips.
10. A liner construction ,for at least a portion of a tube-like wall of a chamber the interior of which is to be subjected to hot gases flowing therethrough; said construction comprising a plurality of elongate strips of sheet metal extending in the general direction of flow through said chamber and forming an internal liner for said wall portion, said strips being disposed in side-by-side relation with a gap between the adjacent longitudinal edges of each pair of adjacent strips, each of said elongate strips having a flange along one longitudinal edge turned toward 1 a corresponding flange along its other longitudi- 7 nal edge and each of said flanges being on the side of its strip facing said wall portion, and a plurality of channel members carried by said wall portion for supporting said elongate strips, each of said channel members having its bottom side facing said wall portion with its open side disposed parallel to, facing and bridging the gap between an adjacent pair of said elongate strips, each of said channel members also having a flange along one of its longitudinal edges extend ing toward a corresponding flange along its other longitudinal edge with each of said flanges being received under the oppositely directed flange of the adjacent elongate strip.
11. A liner construction for at least a portion of a tube-like wall of a chamber the interior of which is to be subjected to hot gases flowing therethrough; said construction comprising a plurality of elongate strips of sheet metal extending in the general direction of flow through said chamber and forming an internal liner for said wall portion, said strips being disposed in side-by-side relation with a gap between the adjacent longitudinal edges of each pair of adjacent strips, each of said elongate strips having a flange along one longitudinal edge turned toward a corresponding flange along its other longitudinal edge and each of said flanges being on the side of its strip facing said wall portion, a plurality of channel members having its bottom side facing said channel members.
12. A liner construction as recited in claim 11 in which said means comprises a plurality of spaced bracket members for supporting each channel member, each bracket member being secured at one end to said wall and at its other end to one of said channel members and being capable of deflecting in a direction parallel to the longitudinal dimension of its channel member to 8 s permit said longitudinal expansion and contraction of said channel members.
13. A liner construction for a wall of a chamber of tapering cross-sectional area the interior of which is to be subjected to hot gases flowing therethrough; said construction comprising a plurality of elongate strips of sheet metal extending in the general direction of gas flow through said chamber and forming an internal liner for said wall, said strips being disposed in side-byside relation with a gap between the adjacent longitudinal edges of each pair of adjacent strips, some of said strips having a constant width between their longitudinal edges and other of said strips having a tapering width and being disposed between said constant width strips; each of said elongate strips having a flange along its other longitudinal edge and each of said flanges being on the side of its strip facing said wall, a plurality of channel members for supporting said elongate strips, eachof said channel members having its bottom portion facing said wall with its open side disposed parallel to, facing and bridging the gap between an adjacent pair of said elongate strips, each of said channel members also having a flange along one of its longitudinal edges extending toward a corresponding flange along its other longitudinal edge with each of said flanges being received under the. oppositely directed flange of the adjacent elongate strip; a plurality of spaced bracket members for supporting each channel member from said wall, each bracket member be-' ing secured at one end to said wall and its other end to one of said channel members and being capable of deflecting in a direction parallel to the longitudinal dimension of its channel member to permit longitudinal expansion and contraction of said channel member.
WALTER W. MAHNKEN.
ROBERT ZECCA..
REFERENCES CITED The following references are of record in the flle of this patent:
UNITED STATES PATENTS Number Name 7 Date 2,245,611 Schultz June 17, 1941 2,395,726 DelTufo Feb. 26, 1946
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US62924A US2544538A (en) | 1948-12-01 | 1948-12-01 | Liner for hot gas chambers |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US62924A US2544538A (en) | 1948-12-01 | 1948-12-01 | Liner for hot gas chambers |
Publications (1)
Publication Number | Publication Date |
---|---|
US2544538A true US2544538A (en) | 1951-03-06 |
Family
ID=22045745
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US62924A Expired - Lifetime US2544538A (en) | 1948-12-01 | 1948-12-01 | Liner for hot gas chambers |
Country Status (1)
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US (1) | US2544538A (en) |
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US2858104A (en) * | 1954-02-04 | 1958-10-28 | A V Roe Canada Ltd | Adjustable gas turbine shroud ring segments |
US2874536A (en) * | 1954-03-18 | 1959-02-24 | Gen Electric | Cooling means for tailpipe |
US2913873A (en) * | 1955-01-10 | 1959-11-24 | Rolls Royce | Gas turbine combustion equipment construction |
US2919549A (en) * | 1954-02-26 | 1960-01-05 | Rolls Royce | Heat-resisting wall structures |
US2955415A (en) * | 1957-11-27 | 1960-10-11 | Theodore M Long | Cooled combustion chamber liner and nozzle supported in buckling modes |
US3038309A (en) * | 1959-07-21 | 1962-06-12 | Gen Electric | Cooling liner for jet engine afterburner |
US3044263A (en) * | 1959-05-21 | 1962-07-17 | Dresser Ind | Combustor with unitary liner |
US3082601A (en) * | 1958-05-08 | 1963-03-26 | Daimler Benz Ag | Rocket combustion chamber |
US3138930A (en) * | 1961-09-26 | 1964-06-30 | Gen Electric | Combustion chamber liner construction |
US3188802A (en) * | 1961-11-29 | 1965-06-15 | Thiokol Chemical Corp | Solid propellant grain |
US3209533A (en) * | 1961-04-21 | 1965-10-05 | John S Light | Rocket shell construction |
US3826088A (en) * | 1973-02-01 | 1974-07-30 | Gen Electric | Gas turbine engine augmenter cooling liner stabilizers and supports |
USB377172I5 (en) * | 1973-07-06 | 1975-01-28 | ||
US3956886A (en) * | 1973-12-07 | 1976-05-18 | Joseph Lucas (Industries) Limited | Flame tubes for gas turbine engines |
US3981609A (en) * | 1975-06-02 | 1976-09-21 | United Technologies Corporation | Coolable blade tip shroud |
US4158949A (en) * | 1977-11-25 | 1979-06-26 | General Motors Corporation | Segmented annular combustor |
US4225054A (en) * | 1977-07-26 | 1980-09-30 | Gaz-Transport | Thermally insulated tank for land storage of low temperature liquids |
US4302932A (en) * | 1979-10-01 | 1981-12-01 | Kuznetsov Andrei L | Annular combustor of gas turbine engine |
US4411134A (en) * | 1981-10-26 | 1983-10-25 | Moir David L | Apparatus for the repair and replacement of transition ducts on jet engines and bracket therefor |
US4422300A (en) * | 1981-12-14 | 1983-12-27 | United Technologies Corporation | Prestressed combustor liner for gas turbine engine |
US4480436A (en) * | 1972-12-19 | 1984-11-06 | General Electric Company | Combustion chamber construction |
US4511536A (en) * | 1982-07-24 | 1985-04-16 | Toyota Jidosha Kabushiki Kaisha | Catalytic converter secondary air supply pipe support |
US4543781A (en) * | 1981-06-17 | 1985-10-01 | Rice Ivan G | Annular combustor for gas turbine |
US4555901A (en) * | 1972-12-19 | 1985-12-03 | General Electric Company | Combustion chamber construction |
US4614082A (en) * | 1972-12-19 | 1986-09-30 | General Electric Company | Combustion chamber construction |
DE3535442A1 (en) * | 1985-10-04 | 1987-04-09 | Mtu Muenchen Gmbh | RING COMBUSTION CHAMBER FOR GAS TURBINE ENGINES |
EP0313464A1 (en) * | 1987-10-21 | 1989-04-26 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Transition channel for a jet engine |
US4854122A (en) * | 1988-01-28 | 1989-08-08 | The United States Of America As Represented By The Secretary Of The Air Force | Augmentor curtain liner assembly for sharing tensile loading |
US4866942A (en) * | 1987-10-13 | 1989-09-19 | The United States Of America As Represented By The Secretary Of The Air Force | Augmentor curtain liner for equalizing pressure therein |
US4907411A (en) * | 1985-06-04 | 1990-03-13 | Mtu Motoren-Und Turbinen-Union Muenchen Gmbh | Internal combustion chamber arrangement |
US4920742A (en) * | 1988-05-31 | 1990-05-01 | General Electric Company | Heat shield for gas turbine engine frame |
FR2649159A1 (en) * | 1989-07-03 | 1991-01-04 | Gen Electric | EXHAUST SHUTTERS |
US5067324A (en) * | 1990-04-04 | 1991-11-26 | United Technologies Corporation | Engine nozzle liner retainer |
DE4309201A1 (en) * | 1993-03-22 | 1994-09-29 | Abb Management Ag | Device for fixing heat accumulation segments of a furnace |
US5363654A (en) * | 1993-05-10 | 1994-11-15 | General Electric Company | Recuperative impingement cooling of jet engine components |
US5499499A (en) * | 1993-10-06 | 1996-03-19 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation | Cladded combustion chamber construction |
US5535585A (en) * | 1994-12-13 | 1996-07-16 | Eichhorn; Gunther | Slotted exhaust liner |
EP0750107A1 (en) * | 1995-06-21 | 1996-12-27 | Volvo Aero Corporation | Exhaust nozzle flap |
EP0843090A3 (en) * | 1996-11-13 | 1999-04-07 | ROLLS-ROYCE plc | Jet pipe liner |
US5910094A (en) * | 1996-09-10 | 1999-06-08 | The Boeing Company | Aircraft labyrinth fire seal |
EP0994304A3 (en) * | 1998-10-15 | 2002-01-02 | United Technologies Corporation | Thermally compliant liner |
US20040011059A1 (en) * | 2001-08-31 | 2004-01-22 | Peter Tiemann | Combustion-chamber arrangement |
US6702549B2 (en) * | 2000-03-02 | 2004-03-09 | Siemens Aktiengesellschaft | Turbine installation |
US20040107690A1 (en) * | 2002-12-06 | 2004-06-10 | Poccia Nicholas Philip | Gas turbine exhaust diffuser |
US20060179770A1 (en) * | 2004-11-30 | 2006-08-17 | David Hodder | Tile and exo-skeleton tile structure |
US20070158527A1 (en) * | 2006-01-05 | 2007-07-12 | United Technologies Corporation | Torque load transfer attachment hardware |
US20070186559A1 (en) * | 2006-02-10 | 2007-08-16 | Snecma | Annular combustion chamber of a turbomachine |
DE102007050664A1 (en) * | 2007-10-24 | 2009-04-30 | Man Turbo Ag | Burner for a turbomachine, baffle for such a burner and a turbomachine with such a burner |
US20090249790A1 (en) * | 2008-04-03 | 2009-10-08 | Snecma Propulision Solide | Gas turbine combustion chamber having inner and outer walls subdivided into sectors |
EP2679780A1 (en) * | 2012-06-28 | 2014-01-01 | Alstom Technology Ltd | Diffuser for the exhaust section of a gas turbine and gas turbine with such a diffuser |
US20140238031A1 (en) * | 2011-11-10 | 2014-08-28 | Ihi Corporation | Combustor liner |
US10072527B2 (en) | 2014-05-23 | 2018-09-11 | General Electric Company | Thermal and acoustic insulation assembly and method for an exhaust duct of a rotary machine |
US10107123B2 (en) | 2013-08-30 | 2018-10-23 | United Technologies Corporation | Sliding seal |
US20180313230A1 (en) * | 2017-05-01 | 2018-11-01 | General Electric Company | Segemented Liner |
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US10240473B2 (en) * | 2013-08-30 | 2019-03-26 | United Technologies Corporation | Bifurcated sliding seal |
US10247106B2 (en) * | 2016-06-15 | 2019-04-02 | General Electric Company | Method and system for rotating air seal with integral flexible heat shield |
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US2245611A (en) * | 1938-05-07 | 1941-06-17 | Frederick W Schultz | Building construction |
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Cited By (75)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2858104A (en) * | 1954-02-04 | 1958-10-28 | A V Roe Canada Ltd | Adjustable gas turbine shroud ring segments |
US2919549A (en) * | 1954-02-26 | 1960-01-05 | Rolls Royce | Heat-resisting wall structures |
US2874536A (en) * | 1954-03-18 | 1959-02-24 | Gen Electric | Cooling means for tailpipe |
US2913873A (en) * | 1955-01-10 | 1959-11-24 | Rolls Royce | Gas turbine combustion equipment construction |
US2955415A (en) * | 1957-11-27 | 1960-10-11 | Theodore M Long | Cooled combustion chamber liner and nozzle supported in buckling modes |
US3082601A (en) * | 1958-05-08 | 1963-03-26 | Daimler Benz Ag | Rocket combustion chamber |
US3044263A (en) * | 1959-05-21 | 1962-07-17 | Dresser Ind | Combustor with unitary liner |
US3038309A (en) * | 1959-07-21 | 1962-06-12 | Gen Electric | Cooling liner for jet engine afterburner |
US3209533A (en) * | 1961-04-21 | 1965-10-05 | John S Light | Rocket shell construction |
US3138930A (en) * | 1961-09-26 | 1964-06-30 | Gen Electric | Combustion chamber liner construction |
US3188802A (en) * | 1961-11-29 | 1965-06-15 | Thiokol Chemical Corp | Solid propellant grain |
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 |
US4555901A (en) * | 1972-12-19 | 1985-12-03 | General Electric Company | Combustion chamber construction |
US3826088A (en) * | 1973-02-01 | 1974-07-30 | Gen Electric | Gas turbine engine augmenter cooling liner stabilizers and supports |
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 |
US3956886A (en) * | 1973-12-07 | 1976-05-18 | Joseph Lucas (Industries) Limited | Flame tubes for gas turbine engines |
US3981609A (en) * | 1975-06-02 | 1976-09-21 | United Technologies Corporation | Coolable blade tip shroud |
US4225054A (en) * | 1977-07-26 | 1980-09-30 | Gaz-Transport | Thermally insulated tank for land storage of low temperature liquids |
US4158949A (en) * | 1977-11-25 | 1979-06-26 | General Motors Corporation | Segmented annular combustor |
US4302932A (en) * | 1979-10-01 | 1981-12-01 | Kuznetsov Andrei L | Annular combustor of gas turbine engine |
US4543781A (en) * | 1981-06-17 | 1985-10-01 | Rice Ivan G | Annular combustor for gas turbine |
US4411134A (en) * | 1981-10-26 | 1983-10-25 | Moir David L | Apparatus for the repair and replacement of transition ducts on jet engines and bracket therefor |
US4422300A (en) * | 1981-12-14 | 1983-12-27 | United Technologies Corporation | Prestressed combustor liner for gas turbine engine |
US4511536A (en) * | 1982-07-24 | 1985-04-16 | Toyota Jidosha Kabushiki Kaisha | Catalytic converter secondary air supply pipe support |
US4907411A (en) * | 1985-06-04 | 1990-03-13 | Mtu Motoren-Und Turbinen-Union Muenchen Gmbh | Internal combustion chamber arrangement |
DE3535442A1 (en) * | 1985-10-04 | 1987-04-09 | Mtu Muenchen Gmbh | RING COMBUSTION CHAMBER FOR GAS TURBINE ENGINES |
US4866942A (en) * | 1987-10-13 | 1989-09-19 | The United States Of America As Represented By The Secretary Of The Air Force | Augmentor curtain liner for equalizing pressure therein |
EP0313464A1 (en) * | 1987-10-21 | 1989-04-26 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Transition channel for a jet engine |
FR2622253A1 (en) * | 1987-10-21 | 1989-04-28 | Snecma | TRANSITION CHANNEL OF A TURBOJECTOR EJECTION ASSEMBLY |
US4974638A (en) * | 1987-10-21 | 1990-12-04 | Societe Nationale D'etude De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Transition pipe for a jet pipe assembly of a turbojet engine |
US4854122A (en) * | 1988-01-28 | 1989-08-08 | The United States Of America As Represented By The Secretary Of The Air Force | Augmentor curtain liner assembly for sharing tensile loading |
US4920742A (en) * | 1988-05-31 | 1990-05-01 | General Electric Company | Heat shield for gas turbine engine frame |
FR2649159A1 (en) * | 1989-07-03 | 1991-01-04 | Gen Electric | EXHAUST SHUTTERS |
US5067324A (en) * | 1990-04-04 | 1991-11-26 | United Technologies Corporation | Engine nozzle liner retainer |
DE4309201A1 (en) * | 1993-03-22 | 1994-09-29 | Abb Management Ag | Device for fixing heat accumulation segments of a furnace |
US5363654A (en) * | 1993-05-10 | 1994-11-15 | General Electric Company | Recuperative impingement cooling of jet engine components |
US5499499A (en) * | 1993-10-06 | 1996-03-19 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation | Cladded combustion chamber construction |
US5535585A (en) * | 1994-12-13 | 1996-07-16 | Eichhorn; Gunther | Slotted exhaust liner |
EP0750107A1 (en) * | 1995-06-21 | 1996-12-27 | Volvo Aero Corporation | Exhaust nozzle flap |
US5713522A (en) * | 1995-06-21 | 1998-02-03 | Volvo Aero Corporation | Exhaust nozzle flap for turbojet afterburner |
US5910094A (en) * | 1996-09-10 | 1999-06-08 | The Boeing Company | Aircraft labyrinth fire seal |
EP0843090A3 (en) * | 1996-11-13 | 1999-04-07 | ROLLS-ROYCE plc | Jet pipe liner |
EP0994304A3 (en) * | 1998-10-15 | 2002-01-02 | United Technologies Corporation | Thermally compliant liner |
US6702549B2 (en) * | 2000-03-02 | 2004-03-09 | Siemens Aktiengesellschaft | Turbine installation |
US20040011059A1 (en) * | 2001-08-31 | 2004-01-22 | Peter Tiemann | Combustion-chamber arrangement |
US6725666B2 (en) * | 2001-08-31 | 2004-04-27 | Siemens Aktiengesellschaft | Combustion-chamber arrangement |
US20040107690A1 (en) * | 2002-12-06 | 2004-06-10 | Poccia Nicholas Philip | Gas turbine exhaust diffuser |
US6807803B2 (en) * | 2002-12-06 | 2004-10-26 | General Electric Company | Gas turbine exhaust diffuser |
US20060179770A1 (en) * | 2004-11-30 | 2006-08-17 | David Hodder | Tile and exo-skeleton tile structure |
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