US2617255A - Combustion chamber for a gas turbine - Google Patents

Combustion chamber for a gas turbine Download PDF

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Publication number
US2617255A
US2617255A US12722A US1272248A US2617255A US 2617255 A US2617255 A US 2617255A US 12722 A US12722 A US 12722A US 1272248 A US1272248 A US 1272248A US 2617255 A US2617255 A US 2617255A
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Prior art keywords
combustion chamber
shells
wall sections
shell
casing
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Expired - Lifetime
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US12722A
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English (en)
Inventor
Niehus Kurt
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BBC Brown Boveri AG Germany
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Bbc Brown Boveri & Cie
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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
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • F23R3/08—Arrangement of apertures along the flame tube between annular flame tube sections, e.g. flame tubes with telescopic sections
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/20—Heat transfer, e.g. cooling
    • F05B2260/221—Improvement of heat transfer
    • F05B2260/224—Improvement of heat transfer by increasing the heat transfer surface
    • F05B2260/2241—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs

Definitions

  • This invention relates to combustion chambers and in particular to those designed for use with gas turbine plants for heating the driving gases.
  • These chambers are customarily located between the compressor outlet and the turbine inlet and the driving gases such as compressed air are heated by introducing fuel into the chamber and burning it in the presence of the compressed air. A portion of the latter is used for combustion of the fuel and the remainder used for cooling the chamber and lowering the gas temperature to the maximum value at which it can be admitted to the turbine without running the risk of damaging the turbine blades by overheating.
  • One type of construction now in use employs a pair of concentric cylindrical shells spaced radially to provide an annular passageway therebetween.
  • the inner shell serves as the combustion chamber proper and is made from a metal which will best withstand the high combustion temperature.
  • a portion of the driving gas such as compressed air is delivered to the inner shell Where it is mixed with the burning fuel to form hot combustion gases, and the remainder is passed through the annular passageway between the shells to take heat from the wall of the inner shell and thereby keep its temperature down.
  • the cooling air is thereafter combined with the gases leaving the combustion chamber and delivered directly to the gas turbine.
  • Another type of construction utilizes a third cylindrical shell between the double shell structure described above, the added shell being bathed on both sides by cooling air and serving to protect the outermost shell from absorbing any appreciable amount of heat.
  • the combustion chamber proper in the form of a plurality of frusto-conical wall sections arranged axially in spaced relation and overlapping so as to provide annular passageways therebetween through which the cooling gases flow to the interior of the chamber.
  • the general object or" this invention is to still further improve upon the cooling of a combustion chamber and specifically so by increasing the amount of surface on the cooling side of the combustion chamber wall in heat exchange relation with the cooling gas.
  • the greatly enlarged surfaces available for the transfer of heat from the combustion chamber wall makes it practical to circulate the cooling gases at a relatively much lower and more economical speed and still assure adequate cooling. Furthermore, the pressure drop of the gases between the inlet and outlet sides of the combustion chamber is kept at a low value by dividing the cooling gases into a plurality of parallel streams, each of which is required to cool only a short section of the combustion chamber wall, the gas streams then being admitted into the combustion chamber where they mix with the products of combustion.
  • Another object is to provide a combustion chamber made up from a plurality of easily renewable wall sections.
  • the latter are also preferably slightly spaced from each other to allow their free expansion in all directions, and are also supported so that they can be replaced easily and quickly when necessary.
  • a further object is to provide a combustion chamber made up from a plurality of closely spaced wall sections, all sections being of like size which not only simplifies storage of replacement parts but also lowers the maintenance cost in replacing any burned out wall section since only one size need be kept on hand.
  • Fig. l is a vertical axial section through a construction in which the combustion chamber proper is constituted by a plurality of cylindrical wall sections of stepped diameter spaced axially in overlapping relation; and Fig. 2 is a transverse section taken on line 22 of Fig. 1.
  • Fig. 1a is a view similar to Fig. 1 with the top portion of the outer surrounding casing modified to provide a second inlet for gas.
  • Fig. 3 is a perspective of one of the arcuate plate sections which when assembled form a completely cylindrical wall of the chamber.
  • Fig. 4 is also a vertical axial section through a slightly different construction in which the several wall sections are frusto-conical shellsof like size rather than cylindrical shells of stepped sizes.
  • Fig. 5 is likewise a vertical axial section through a construction in which the several axially spaced wall sections forming the complete combustion chamber proper are cylindrical shells of uniform diameter with their upper ends flared outwardly.
  • Fig. 6 is an axial section through still another form of the invention featuring open-ended shells of like size, each of which is constituted by an assembly of flat-sided wall sections that form a combustion chamber of polygonal cross section;
  • Fig. 7 is a half-transverse section taken on line 1-1 of Fig. 6; and
  • Fig. 8 is a perspective of one of the wall sections used in the Fig. 6 construction.
  • Figs. 9, 10, l1 and 12 are views of still other constructions for the wall of the combustion chamber within the scope of the present in- Vention.
  • the combustion chamber in general includes an outer gas-pressure resistant casing I having an inlet I I at the top for gas which, in an application of the combustion chamber to gas turbine plants, would lead to the high pressure outlet of the air compressor unit, not shown.
  • the bottom end I2 of casing ID is open and, again assuming the same application, would lead to the inlet side of the gas turbine unit, also not shown, that drives the useful load and the compressor unit.
  • the combustion chamber proper is comprised of an assembly of open-ended cylindrical shells I3a, I31), I30 of stepped and decreasing diameter mounted one above the other in overlapped relation inside of casing Ill.
  • Each shell as shown by the transverse sectional view Fig. 2, is sectionalized peripherally so as to be constituted by a plurality of arcuate wall sections I4 arranged in side-by-side relation, one of which is shown in perspective in Fig. 3.
  • the side edges of these wall sections extend longitudinally of the axis of the combustion chamber and the confronting side edges of adjacent sections are spaced slightly apart to allow for free expansion in all directions.
  • the exterior surface of each wall section is ribbed in an axial direction at Mo to provide longitudinal grooves or passageways I for cooling gas which takes on the heat from the plate portion Mb and thus serves to keep its temperature down to a safe level.
  • each of the inner shells I3a-I3c Surrounding closely each of the inner shells I3a-I3c is an outer open-ended cylindrical shell I6 made in one piece. Each of the latter is secured in place by attachment to a spider II that is in turn supported at the wall of the outer casing II]. Each of the outer shells supports its associated inner shell and for this purpose has slots I8 for receiving .the toeportion of hook type hangers I9 secured to the end ribs I la of each wall section I4.
  • each of the outer shells underlaps and lies in contact with the interior surface of the inner shell next below it.
  • cooling air entering the top of any of the annular ribbed .passageways 23 passes out of the lower end of the passageway into the interior of the inner .shell .next below it along the interior surface of the latter.
  • Located at the top of the uppermost inner shell I30 .is a nozzle 2
  • the construction shown in Fig. 1 has many advantages.
  • the axially extending ribs Ma at the exterior surface of the wall sections l4 greatly enlarge the area available for surface contact with the cooling air and thus materially improve the rate at which heat is transferred from the hot interior surface of the overlapped inner shells that are subjected to the extremely high combustion temperatures. This makes it possible to keep the temperature of the inner shells down to a safe level without resorting to high velocities of air flow along the ribs which, for reasons already stated, should be avoided in the interest of high efficiency operation.
  • the pressure difference required to send the cooling air along the ribbed walls will be approximately the same as the pressure drop in the combustion air as it passes through the vanes 22.
  • each of the inner shells I3a,-I3c from a plurality of wall sections I4 is also of advantage, for replacement of one or more of the sections in the event of a burn-out is obviously far more economical than would be the case were the entire shell to be renewed.
  • the hook-andslot type support for the plate sections makes replacement a simple and brief task and, what is equally important, each of the wall sections is able to expand freely in all directions.
  • Fig. la The construction shown in Fig. lais quite similar to that of Figs. 1-3. The only differences are that the upper end of the outer casing Iil is blocked off by a transverse partition 24 so that all of the air delivered at the inlet II passes through the vanes 22 into the upper shell I30, and a second gas inlet 25 is provided immediately beneath partition 24 that communicates with the spaces between the outer casing l0 and the shells ISa-l3c and it.
  • This type of combustion chamber is especially suited for use in the production of heating gas for a steam boiler plant or as a superheater.
  • Air for combustion would be supplied to air inlet H from a blower, the air entering through vanes 22 and serving to support combustion of fuel discharged into the combustion chamber shells Ilia-I30 from nozzle 2i. Flue gas would be introduced through inlet 25, the latter passing downwardly along the ribbed plate section! for cooling the latter and entering the combustion chamber proper as in the case of the construction shown in Fig. 1.
  • Fig. 4 illustrates a modified embodiment of a combustion chamber incorporating the invention that permits all of the inner and outer shells to be of the same construction and dimensions. This is an advantage in manufacture since it reduces the number of different parts required. It also simplifies replacement and storage problems in that only one size of outer shell and inner wall section need be stocked.
  • each of the inner shells 26a, 26b and 260 is comprised of a frusto-conical assembly of closely spaced wall sections 2? the exterior surfaces of which are ribbed axially at 28 as in Fig. 1.
  • An outer one-piece frusto conical shell 29 closely surrounds each of the inner shells to form an annular gas pasageway 3i that is likewise of frusto cone form.
  • Each of the shells 29 is provided with slotted apertures 32 which receive the support hooks 33 of the associated inner wall sections 27.
  • a ring 3d welded or otherwise secured in place inside the outer cylinrdical casing 35 is provided to support the vertical assembly of inner and outer shells.
  • each of the outer shells 29 is provided with a plurality of circumferentially spaced lugs 36.
  • Lugs 36 for the lowermost outer shell 29 rest upon ring 34 and the lugs of each of the remainder of the outer shells 29 rest upon the upper end face of the shell next below it.
  • the support lugs 36 are so placed upon the outer shells 29 that the latter and the inner shells overlap as in the Fig. 1 construction.
  • each of the outer shells lies adjacent the interior surface of the inner shell next below it so that the cooling gas upon leaving one of the annular passageways 3! W111 move into the combustion chamber along the interior surface of the next inner shell below it in the assembly.
  • FIG. 5 Another constructional form of the invention which affords a near maximum space for combustion inside the casing and also permits the superposed shell assembly to be made from sections of like dimensions is illustrated in Fig, 5.
  • each of the inner shells 37a, 37b, 310 which are positioned one above the other in spaced rather than in telescoping relation, is cylindrical and composed of an assembly of arcuate wall sections 38 having ribs 39 on their exterior surface and hooks $1 for hanging each of the sections in position over the upper end of the closely surrounding outer and one piece cylindrical shell 52.
  • the latter which are all of like diameter are provided with a plurality of radially extending cars 43 for attachment to vertical supports 44 placed within the cylindrical casing 45.
  • each wall section 38 is turned outwardly so that when assembled to form the inner shell, the latter will have a flared opening at its upper end positioned immediately below the inner shell right above it in the assembly. Furthermore the internal diameter of the shell at its upper flared end is made substantially the same as the exterior diameter measured at the outer edges of the ribbed exterior surface along the main body portion of the shell so that cooling air flowing along the ribbed passageway of one of the inner shells will pass into the flared opening of the shell next below it and thence into the combustion space.
  • each of the inner shells (lea-ted is constructed in polygonal form from a group of fiat, externally ribbed wall sections 41, there being one plate section to each side of the polygon.
  • the inner shells are all supported in spaced relation one above the other by a closely surrounding one piece outer shell 48 which can be cylindrical, the latter being provided with slots to receive the hangers 58 at each side of each wall section.
  • the ribs is which make up the outer channeled surface of each inner shell are interrupted at a point substantially midway between the ends and a peripheral opening 5
  • the incoming cooling air divides about in half, one half passing upwardly along the ribbed outer surface of the inner shell and thence over the upper edge into the combustion space, and the other half passing downwardly along the ribbed surface of the shell and thence into the inner shell next below.
  • the reason for providing an interruption in the ribbed exterior surface of the inner shell becomes apparent when one considers the fact that the large temperature drop transversely across the ribs results in different expansion characteristics at different points along the ribs as measured in this direction.
  • the very hot plate portion Ala expands much more than does the outer and much cooler edge 49a of the ribs so that the whole ribbed body tends to twist lengthwise.
  • the ribbed wall sections are illustrated as being formed from a solid body, the ribs themselves being milled out for example. Because of the extremely high temperatures prevailing within the combustion chamber proper, a material having a high degree of resistance to heat is preferred and chromium steel has been found suitable. Instead of machining grooves in solid material to form the ribs and wall portions of each wall section, one can start from a fiat plate of chromium steel and by folding it reversely back and forth upon itself as shown in Fig. 9 produce a substantially arcuate or flat wall portion 53 as the case may require, and ribs 5-! between which the cooling air will flow.
  • FIG. 1 Another practical construction for the wall sections of each of the inner shells is shown in Fig.
  • aeivgens 7 10.
  • the wallportionuproperiisz comprisedof a relatively thick plate or 'chromiumtsteel to which is'attached on the:exterior surfacea much thinner steel plate 56 :bent back 'and forth .upon itself tofform hollow cooling ribsfil.
  • the hollow ribs 51 are then cast'full of copper 58 or some other material likewise notabl'e'for its "high'heat conduction characteristic.
  • the plate section 59 with the arcuateplateportion 60 carries ribs'ol onthe exterior. surface, the inlet end Bla of which is higher than the outlet end 61b. This means that the cross-section of thelongitudinalgrooves 62 is greater at their inlet end than at their outlet end. The velocity of the cooling air increases as it flows through the grooves and,'although its temperature increases also, the rate of heat transfer can bemaintained.
  • Fig. 11 further illustrates a construction with hooks 53 located on the middle rib, a feature which facilitates free'lateral expansion of the plate sections.
  • the platesections 64a, 64b and Ma consisting of plates 65-and ribs fifi with decreasing height, are held by frusto-conical rings 61 by means of hooks 68 and slots 69.
  • the lowermost conical ring, by means of lugs Til rests on a ring ll attached to the inside of the outer cylindrical casing 12; the upper conical rings rest upon the upper end faces of the rings next below themby means of similar lugs.
  • a combustion chamber comprising inner-and outer shell members spaced from each other to provide a passageway therebetween for cooling gases, said inner shell member being sectionalized peripherally into a plurality of wall sections the side edges of which extend longitudinally of the chamber, said wall sections being arranged in side-by-side relation with the-side edges of adjacent wall sections spaced from each other, each said wall section being provided with ribs extending longitudinally along the outer surface-thereof, hanger means individual to each of said wall sections supporting the latter independently in said spaced relation upon said outer shell member to thereby permit said spaced wall sections to expand independently of the other wall sections adjacent thereto, and means for admitting fuel and a combustion supporting medium into said inner shell member for combustion.
  • each of the wall sections comprising said inner shell member is made from metallic plate material and said ribs areproduced by folding 8 successive portions of said material back :and forth'uponitself.
  • Alcombustion chamber comprising a casing, a plurality of open ended inner shells arranged in spaced relation one above the other in said casing, each of said shells being constituted by a peripheral assembly of wall sections the side edges of which extend longitudinally of said casing, said wall sections being arranged in sideby-side relation with the side edges ofiadjacent wallsections spaced from each other, each said wall'section having ribs extending longitudinally along theouter surface thereof, means for introducing fuel and a combustion supporting medium into the space enclosed by said inner shells for combustion, an outer shell closely surrounding each of'said'inner shells to provide a passageway for leading cooling gases along the surfaces of said ribs, and'hanger means individual to each of said wall sections supporting the latter independently in said spaced relation upon the surrounding outer shells to thereby permit the spaced Wall sections constituting each inner shell to-expand independently of the'other wall sections adjacent thereto.
  • a combustion chamber comprising a casing having a top air inlet and a bottom air outlet, a plurality of open-ended inner'shells of stepped cross section arranged one above the other in said casing in partly telescoped relation, said shells decreasing in cross-section in the direction of the air inlet to said casing, each of said inner shells being comprised of a peripheral assembly of wall sections the side edges of which extend longitudinally of said casing, said wall sections being arranged inside-by-side relation with the side edges of adjacentwall sections spaced from each other, each said wall section having ribs extending longitudinally along the outer surface thereof, an open-ended outer shell closely surrounding each'of said inner shells to form a plurality of steppedgas passageways therebetween each of which receives cooling'air at the upper end and dischargesthe same'at the lower end inside the next lower inner shell, hanger means individual to each ofsaid wall sectionssupporting the latter independently in said spaced relation upon the surrounding outer shells to thereby permit the spaced wall sections constituting each inner shell to'exp
  • a combustion chamber comprising an outer casing, an inlet for cooling gas at the upper end of said casing, a gas outlet at the lower end of said casing, a plurality of open-ended cylindrical inner shells of stepped diameters assembled one above the other in said casing, said shells decreasing in diameter in the direction of the air inlet to said casing and overlapping one another, each of said inner shells being comprised of a peripheral assembly of wall sections the side edges of which extend longitudinally of said casing, said wall sections being arranged in side-byside relation with the side edges of adjacent wall sections spaced from one another, each said wall section having ribs extending longitudinally along the outer surface thereof, an open-ended outer shell closely surrounding each of said inner shells and which extends into the inner shell next below adjacent its interior surface to establish an annular passageway between each inner and outer shell for downward flow of cooling gas in said casing along the ribbed surface of one inner shell into the inner shell next below, hanger means individual to each of said wall sections supporting the latter independently in said spaced relation upon the surrounding outer
  • a combustion chamber comprising a casing, an inlet for gas at the upper end of said casing, a plurality of like open-ended inner shells arranged one above the other in said casing in partly telescoped relation and tapered outwardly in the direction of said gas inlet, each of said inner shells being comprised of a peripheral assembly of wall sections the side edges of which extend longitudinally of said casing, said wall sections being arranged in side-by-side relation with the side edges of adjacent wall sections spaced from each other, each said wall section having ribs extending longitudinally along the outer surface thereof, an open-ended outer shell closely surrounding each of said inner shells to form gas passageways therebetween, each said passageway receiving cooling gas at the upper end and discharging the same at the lower end inside of the next lower inner shell, hanger means individual to each of said wall sections supporting the latter independently in said spaced relation upon the surrounding outer shells to thereby permit the spaced wal1 sections constituting each inner shell to expand independently of the other wall sections adjacent thereto, and means for admitting fuel and a
  • a combustion chamber comprising a casing, a plurality of open-ended inner shells uniform in cross-sectional area arranged in spaced relation one above the other in said casing, each of said inner shells being comprised of a peripheral assembly of wall sections the side edges of which extend longitudinally of said casing, said wall sections being arranged in side-by-side relation with the side edges of adjacent wall sections spaced from each other, each said wall section having ribs extending longitudinally along the outer surface thereof, an outer shell spaced inwardly from said casing and closely surrounding said inner shells to provide a passageway for cooling gas admitted to said casing, said outer shell being provided with a peripheral opening adjacent the middle of each inner shell for admitting cooling gas part of which flows upwards and part downwards along the ribbed surface into the interior of said inner shells through the spaces therebetween, hanger means individual to each of said wall sections supporting the latter in spaced relation upon the surrounding outer shell to thereby permit the space-d wall sections constituting each inner shell to expand independently of the other wall sections adjacent thereto, and
  • a combustion chamber comprising an outer casing having an inlet for cooling gas at the upper end and a gas outlet at the lower end, a plurality of open-ended inner shells arranged in spaced relation one above the other in said casing, each of said inner shells being comprised of a peripheral assembly of wall sections the side edges of which extend longitudinally of said casing, said wall sections being arranged in side-by-side relation with the side edges of adjacent wall sections spaced from each other, each said wall section having ribs extending longitudinally along the outer surface thereof and the upper portion of each said wall section being flared outwardly in the direction of said gas inlet to provide a mouth portion for receiving cooling gas flowing between the ribs of the shell next above, an open-ended outer shell closely surrounding each of said inner shell, hanger means individual to each of said wall sections supporting the latter independently in said spaced relation upon the surrounding outer shells, hanger means individual to each of said constituting each inner shell to expand independently of the other wall sections adjacent thereto, and means for admitting fuel and a combustion supporting medium into the

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
  • Combustion Of Fluid Fuel (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US12722A 1947-05-12 1948-03-03 Combustion chamber for a gas turbine Expired - Lifetime US2617255A (en)

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CH647293X 1947-05-12

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GB (1) GB647293A (de)

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US20100205969A1 (en) * 2007-10-24 2010-08-19 Man Turbo Ag Burner for a Turbo Machine, Baffle plate for Such a Burner and a Turbo Machine Having Such a Burner
WO2012134816A1 (en) * 2011-03-29 2012-10-04 Siemens Energy, Inc. Turbine combustion system liner
US8307654B1 (en) * 2009-09-21 2012-11-13 Florida Turbine Technologies, Inc. Transition duct with spiral finned cooling passage
US8402764B1 (en) * 2009-09-21 2013-03-26 Florida Turbine Technologies, Inc. Transition duct with spiral cooling channels
CN105318356A (zh) * 2014-07-21 2016-02-10 北京航天动力研究所 一种大深宽比变截面换热通道
US11506384B2 (en) 2019-02-22 2022-11-22 Dyc Turbines Free-vortex combustor

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FR2440524A1 (fr) * 1978-11-03 1980-05-30 Gen Electric Chambre de combustion diminuant les emissions de gaz
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DE3113380A1 (de) * 1980-04-02 1982-04-08 United Technologies Corp., 06101 Hartford, Conn. Einsatz fuer den brenner eines gasturbinentriebwerks
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FR2479901A1 (fr) * 1980-04-02 1981-10-09 United Technologies Corp Garniture interieure de chambre de combustion pour une turbine a gaz
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US4419863A (en) * 1981-09-30 1983-12-13 United Technologies Corporation Fuel-air mixing apparatus
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US5653110A (en) * 1991-07-22 1997-08-05 General Electric Company Film cooling of jet engine components
US5353587A (en) * 1992-06-12 1994-10-11 General Electric Company Film cooling starter geometry for combustor lines
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EP1001221A3 (de) * 1998-11-12 2002-07-10 Mitsubishi Heavy Industries, Ltd. Kühlstruktur für eine Gasturbinenbrennkammer
EP1211463A3 (de) * 2000-12-04 2003-07-23 Mitsubishi Heavy Industries, Ltd. Rippenplatte und Brennkammer mit der Rippenplatte
US20090100838A1 (en) * 2007-10-23 2009-04-23 Rolls-Royce Plc Wall element for use in combustion apparatus
US8113004B2 (en) * 2007-10-23 2012-02-14 Rolls-Royce, Plc Wall element for use in combustion apparatus
US20100205969A1 (en) * 2007-10-24 2010-08-19 Man Turbo Ag Burner for a Turbo Machine, Baffle plate for Such a Burner and a Turbo Machine Having Such a Burner
US20090173416A1 (en) * 2008-01-08 2009-07-09 Rolls-Royce Plc Gas heater
US8617460B2 (en) 2008-01-08 2013-12-31 Rolls-Royce Plc Gas heater
US8256224B2 (en) 2008-02-01 2012-09-04 Rolls-Royce Plc Combustion apparatus
US20090193813A1 (en) * 2008-02-01 2009-08-06 Rolls-Royce Plc Combustion apparatus
US20090229273A1 (en) * 2008-02-11 2009-09-17 Rolls-Royce Plc Combustor wall apparatus with parts joined by mechanical fasteners
US8408010B2 (en) 2008-02-11 2013-04-02 Rolls-Royce Plc Combustor wall apparatus with parts joined by mechanical fasteners
US20090214354A1 (en) * 2008-02-26 2009-08-27 Rolls-Royce Plc Nose cone assembly
US8529204B2 (en) 2008-02-26 2013-09-10 Rolls-Royce Plc Gas turbine engine having a nose cone assembly rigidly attached in an axial direction but flexible in a radial direction
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US8622737B2 (en) * 2008-07-16 2014-01-07 Robert S. Babington Perforated flame tube for a liquid fuel burner
US20100015562A1 (en) * 2008-07-16 2010-01-21 Babington Robert S Perforated flame tube for a liquid fuel burner
US9234659B2 (en) 2008-07-16 2016-01-12 Robert S. Babington Perforated flame tube for liquid fuel burner
US8402764B1 (en) * 2009-09-21 2013-03-26 Florida Turbine Technologies, Inc. Transition duct with spiral cooling channels
US8307654B1 (en) * 2009-09-21 2012-11-13 Florida Turbine Technologies, Inc. Transition duct with spiral finned cooling passage
US20120247111A1 (en) * 2011-03-29 2012-10-04 Narcus Andrew R Turbine combustion system liner
WO2012134816A1 (en) * 2011-03-29 2012-10-04 Siemens Energy, Inc. Turbine combustion system liner
CN103547866A (zh) * 2011-03-29 2014-01-29 西门子能量股份有限公司 涡轮燃烧系统衬垫
US8955330B2 (en) * 2011-03-29 2015-02-17 Siemens Energy, Inc. Turbine combustion system liner
CN105318356A (zh) * 2014-07-21 2016-02-10 北京航天动力研究所 一种大深宽比变截面换热通道
US11506384B2 (en) 2019-02-22 2022-11-22 Dyc Turbines Free-vortex combustor

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GB647293A (en) 1950-12-13
DE863153C (de) 1953-01-15
CH255541A (de) 1948-06-30

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