US2636345A - Gas turbine combustor having helically directed openings to admit steam and secondary air - Google Patents

Gas turbine combustor having helically directed openings to admit steam and secondary air Download PDF

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Publication number
US2636345A
US2636345A US15832A US1583248A US2636345A US 2636345 A US2636345 A US 2636345A US 15832 A US15832 A US 15832A US 1583248 A US1583248 A US 1583248A US 2636345 A US2636345 A US 2636345A
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Prior art keywords
wall
combustion
space
combustion chamber
casing
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Expired - Lifetime
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US15832A
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English (en)
Inventor
Zoller Ronald Ernest
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Babcock and Wilcox Co
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Babcock and Wilcox Co
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
    • F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
    • 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
    • F23M5/08—Cooling thereof; Tube walls
    • 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
    • F23R3/005—Combined with pressure or heat exchangers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/25—Three-dimensional helical

Definitions

  • This invention relates to furnaces and particularly to furnaces adapted to operate under pressure and suitable for supplying hot gases to gas turbines.
  • combustion Within a gas turbine furnace must take place at high temperature. There is therefore not only a considerable internal pressure, but also a high temperature within the furnace, with a result that gas. turbine furnaces have suffered from low availability.
  • Particularly diflicult conditions arise when a furnace is arranged to effect interstage reheating since the gases entering the furnace are already at a substantial temperature.
  • An object of the invention is the provision of furnaces of improved reliability.
  • the present invention comprises a furnace for the generation of gases under pressure for a gas turbine having a combustion space which is surrounded by a wall faced internally with refractory material in which are embedded metal elements projecting inwardly towards the combustion space from tubes adapted for the flow of coolingfluid therethrough and which is enclosed within a metal casing adapted to resist pressure and at a distance from the wall to leave a space between the casing and the wall at least part of which space is occupied by a passage surrounding the combustion space and adapted for the flow of cooling gaseous fluid therein.
  • the metal elements may include studs arranged for keying or holding the refractory material, most suitably chrome ore. Fins or other extended surface elements may be used as the metal elements.
  • the invention moreover includes alfurnace comprising a casing adapted to withstand internal pressure and a tubulous jacket surrounding a combustion space within the casing and adapted to conduct cooling fluid and discharge thefluid into the furnace gases.
  • the invention furthermore includes a furnace comprising a casing adapted to withstand internal pressure, an inner hollow jacket surrounding a combustion space within the casing and adapted to conduct cooling fluid, an outer hollow jacket spaced from the inner jacket and from the casing and adapted to conduct coolingfluid, common means for supplying gaseous fluid to the combustion space and to the space between the jackets and separate means for supplying gaseous fluid to the spacebetween the outer jacket and the casing.
  • the invention furthermore includes a furnace comprising a casing adapted to withstand internal pressure, a hollow jacket surrounding a combustion space within the casing and adapted to conduct cooling fluid, means for adding cooling gaseous fluid to the products of combustion and means for providing a mixing jet or mixing jets of elastic fluid adapted to promote mixing of the cooling gaseous fluid and products of combustion.
  • Figure 1 represents partly diagrammatically a longitudinal cross-section of a furnace for the generation of gases for a high-pressure gas turbine;
  • Figure 3 is to a larger scale than Figures 1 and 2 and shows the arrangement of studs on the surfaces facing towards the combustion space of tubes of the wall surroundin the combustion space, as seen before the application of refractory thereover;
  • Figure 4 shows a cross-section on the line IVIV of Figure 3, and shows also refractory in place over the tube surfaces.
  • the furnace chamber 2 comprises a pressure resisting casing 30 of genof the pressure casing.
  • the cooled-wall structure a steam cooled wall structure 3i having a cylindrical wall 32 spaced from the cylindrical wall of the pressure casing.
  • the cooled wall structure is formed'at one end with a firing opening 33 centrally within which is arranged a steam atomising oil burner I3 having an impeller plate 34 around the nozzle thereof and designed to cause air entering the combustion space immediately around the nozzle to have a whirling motion around the nozzle, and provided with the usual adjustable louvres 35 between which flows the air arranged to enter through the firing opening into the combustion space 56 within the cooled wall structure, and at its other end the cooled wall structure is formed with an opening 37 for the exit of gases from the combustion space.
  • the cylindrical wall 32 of the cooled wall structure and the end wall 38 at the end of the combustion space around the exit opening are formed by chrome ore refractory material 200 ( Figure 4) applied while in a plastic condition over the surfaces facing inwardly towards the combustion space of twenty-four tube coils 39, such surfaces being provided with metal studs iiili ( Figures 3 and 4; the scale of Figure 1 does not allow the studs to be represented therein).
  • Part of one of the tube coils 39 is arranged to define the end wall 48 of the combustion space around the firing opening.
  • a further tube coil ll is arranged to form a passage 32 with converging walls through which the gases from the combustion space must flow before reaching the exit opening.
  • the pressure casing is formed with an internally extending portion 43 forming a diverging passage is for the gases leaving the combustion space 3E, and the walls of such passage are also lined with the tube coil 4!.
  • the pressure casing is formed with a flange 2H) for mounting the furnace on a gas turbine casing.
  • the various tube coils are cooled by the passage therethrough of steam led thereto by an inlet 45 extending through the pressure casing into a header 46 which is arranged longitudinally in the pressure casing and into which the steam inlet ends of the tube coils connect.
  • Each tube coil is led in the cylindrical and end walls of the cooled wall structure a suitable number of times around the axis of the combustion space and terminates in a steam outlet nozzle 47 arranged to deliver steam passing through the coil into the combustion space with a whirling motion therearound in the same direction as the whirling motion of air produced by the impeller plate 34 and as a stream flowing initially at least in part in contact with the adjacent wall.
  • the nozzles 41 in which the tube coils 39 of the cylindrical and end walls terminate are arranged in four rows spaced longitudinally of the combustion space with six nozzles in each row spaced evenly around the cylindrical wall 32.
  • around the converging passage to the exit opening and the diverging passage therefrom terminates in a nozzle 41 arranged to deliver into the gases shortly after they have entered the converging passage and in a stream initially at least partly in contact with the walls of the passage and having a whirling motion around the passage in the same direction as the whirling motion of air produced by the impeller plate 34.
  • the pressure casing is formed at the gas exit end thereof with an inlet 48 for the entry of compressed air supplied by a high pressure compressor.
  • the air led to the furnace chamber cools the pressure casing and after entering the combus tion space 35 ensures complete combustion and dilutes and cools the products of combustion issuing from the furnace chamber to the gas turbine.
  • the steam supplied effects a cooling of the wall structure 31 therein by flowing through the tubes thereof and also, after being injected into the combustion chamber by the nozzles, by flowing more or less mixed with air and products of combustion over the inner surface of the cylindrlcal wall 32 with a whirling motion around the combustion space, and effects turbulence which promotes the passage to the turbine of well-mixed unstratified gases.
  • the number and design of the steam nozzles are such that a steam pressure not considerably greater than that in the furnace chamber 2 is sufficient to provide the required how of steam.
  • the furnace chamber 4 comprises a pressure resisting casing 89 of generally cylindrical form having arranged therein two cooled wall structures 8i and 82 spaced from one another and from the cylindrical walls of the pressure casing.
  • the inner cooled wall structure 82 is formed at one end with a firing opening 83 centrally within which is arranged a steam atomising oil burner 14 having an impeller plate 84 arranged around the nozzle thereof and designed to cause the air flowing immediately adjacent the nozzle towards the combustion space to have a whirling motion around the nozzle, and provided with the usual adjustable louvres 85 between which flows the air arranged to enter through the firing opening into the combustion space 88 within the inner cooled wall structure 82, and at the other end the cooled wall structure is formed with an opening 87 for the exit of gases from the combustion space.
  • the cylindrical walls 88 of the inner cooled wall structure and the end wall 89 at the end of the combustion space around the exit opening are formed by chrome ore refractory material applied while in a plastic condition over the surfaces facing inwardly towards the combustion space of twenty-four tube coils 98, such surfaces being provided with studs in the same manner as the tubing 39 of Figures 3 and 4.
  • Part of one of the tube coils 98 is arranged to define the end wall 9! of the combustion space around the firing opening.
  • a further tube coil 92 arranged to form a passage 93 with converging walls through which the gases from the combustion space must flow before reaching the exit opening.
  • the pressure casing is formed with an internally extending portion 94 forming a diverging passage 95 for the gases leavin the combustion space, and the walls of such passages are also lined with the tube coil 92.
  • the pressure casing is formed with a flange 220 for mounting the furnace on a gas turbine casing.
  • the various tube coils are cooled by the passage therethrough of steam led thereto by an inlet 96 extending through the pressure casing into a header 9'! which is arranged longitudinally in the pressure casing in the space 98 between the inner and outer cooled wall structures.
  • Each tube coil is led a suitable number of times around the axis of the furnace chamber and terminates in a steam outlet nozzle 99 arranged to deliver steam which has passed through the coil into the combustion space with a whirling motion therearound in the same direction as the whirling motion of air produced by the impeller plate 84, and as a stream flowing initially at least in part in contact with the adjacent wall.
  • the nozzles 99 in which the tube coils 90 of the cylindrical and end walls of the inner cooled wallstructure terminate are arranged in four rows spaced longitudinally of the cylindrical wall with six nozzles in each row spaced evenly around the wall.
  • the tube coil 92 around the converging passage 93 to the exit opening 81 and the diverging passage 95 therefrom terminates in a nozzle 99' arranged to deliver into the gases shortly after they have entered the converging passage and in a stream initially at least partly in contact with the wall of the passage and having a whirling motion around the passage in the same direction as the whirling motion of air produced by the impeller plate 84.
  • extends longitudinally in the casing at one end as far as the end wall 89 in which the exit opening 81 is formed, and at the other end to about as far as the louvres 85 of the burner.
  • an inlet I I0 is formed for the admission of compressed air supplied by a low pressure compressor to the annular space I l I between the outer cooled wall structure 81 and the pressure casing at the end of the space remote from the burner. From the air inlet III] the air is arranged to flow in the annular space III towards the burner and a part of the air enters the combustion space through the firing opening 83. The remainder of the air enters the annular space 98 between the cooled wall structures.
  • the outer cooled wall structure 8I includes twenty-four tube coils [I2 cooled by the steam from the steam header 91, and these tube coils are so connected in the steam flow that the steam flows in twenty-four parallel flow paths from the steam header first into the tube coils H2 of the outer cooled wall structure 8
  • the pressure casing is formed at the gas exit end thereof with an inlet II3 for the entry of gases from a high pressure gas turbine.
  • gases One part of these gases is arranged to flow into the stream of gases flowing from the exit opening, through eight apertures H4 formed in the Wall of the diverging passage 95 and arranged in pairs evenly spaced around the passage. The remainder of the gases is arranged to flow into the annular space 98 between the cooled wall struc ture.
  • gaseous fluid enters the combustion space with a whirling motion therearound in the same direction as the whirling motion of air produced by the impeller plate 84, by flowing through inclined ports I I5 formed in the cylindrical wall 88 of the inner cooled wall structure.
  • the ports are arranged in three rows spaced longitudinally of the combustion space and the six ports in each row are spaced evenly around the Wall.
  • the furnaces described are adapted for long availability and for adequate cooling with high combustion temperatures for ensuring rapid combustion of oil.
  • a metallic pressure resisting casing in the formation of a wall within the casing and spaced therefrom to provide a passage for the flow of cooling gaseous fluid, metallic studs integral with the metal of the tubes and projecting from the sides of the tubes opposite said casing,.high temperature refractory material covering thestuds and the inner faces of the tubes to form the face of the wall of the combustion chamber, the wall of the combustion chamber being formed with a plurality of inclined ports for the admission into the combustion space of cooling gaseous fluid with a whirling motion from the passage outside the wall, means for firing the combustion chamber, means for discharging cooling fluid from said tubes into the furnace gasesin the combustion space before the gases leave the furnace, said last name-d means being arranged to discharge fluid with a whirling motion around the combustion space, means for providing said tubes with a cooling fluid, and means providing a furnace gas outlet from the combustion space, said last named means including a wall projecting into
  • a metallic pressure resisting casing In a furnace for the generation of gases under pressure for a gas turbine, a metallic pressure resisting casing, fluid conducting tubes arranged in the formation of a wall within the casing and spaced therefrom to provide a passage for the flow of cooling gaseous fluid, me-
  • combustion chamber wall means including contiguous wall tubes normally providing for the flow of cooling fluid therethrough, the wall means also includingmetallicextended surface elements secured in good heat transfer relationship to the tubes and projectingfrom the combustion chamber sides of the tubes, high temperature refractory material covering-the sides of the tubes toward the combustion chamber face of the wall means, burner means firing the combustion chamber, a metallic pressure resistant casing enclosing the combustion chamber and spaced outwardly therefrom to provide a combustion chamber encompassing space, second wall means including similar wall tubes-for the how of cooling fluid therethrough, said second wall means being disposed at a position intermediate the first wall means and the casingand dividing said space into twocombustion chamber enveloping spaces, and normally directing the how of a gaseous cooling medium to said spaces and from said spaces to the combustion chamber at distributed positions and to the firing means.
  • combustion chamber wall means including contiguous wall tubes normally providing for the flow of cooling fluid therethrough, the wall means also including metallic extended surface elements secured, in good heat transfer relationship to the tubes and projecting from the combustion chamber sides of the tubes, high temperature refractory material covering the sides of the tubes toward the combusticn chamber face of the wall means, burner means firing the combustion chamber, a metallic pressure resistant casing enclosing the combustion chamber and spaced outwardly'thereirom to provide a combustion chamber encompassing space, second wall means including similar wall tubes for the flow of cooling fluid therethrough, said second Wall means being disposed at a position intermediate the first wall means and the casing and dividing said space into two combustion chamber enveloping spaces, said firing means including a device imparting a whirling motion to the gases within the combustion chamber, angularly directed nozzles fed with fiuidby said tubes and directedso asto augment the whirling motion of the gases within the coin bustion chamber by
  • cylindrical combustion chamber wall means including contiguous wall tubes normally having steam flow therethrough, the wall means also including metallic extended surface elementssecured in good heat transfer relationship to the tubes and projecting from the combustion chamber-sides of the tubes, high temperature refractory material covering the sides of the tubes toward the combustion chamber and surrounding the studs.
  • combustion chamber face of the wall means, burnermeans firing the combustion chamberwith a whirling motion ofv the combustion elements, a metallic pressure resistant cylindrical casing en closing the combustion chamber and spaced outwardly therefrom to provide a combustion chamber encompassing space, means normally directing the flow of a gaseous cooling medium to said space and from said space to the firing means and to the combustion chamber at distributed positions, inclined nozzles fed by the steam heating tubes and so directed through the combustion chamber wall at distributed positions as to augment the whirling action initiated by the firing means, and a gas mixing combustion chamber outlet of venturi-like construction involving similar steam heating wall tubesand a similarly: inclined steam nozzle.
  • hollow cylindrical combustion chamber wall means including contiguous wall tubes normally'having steam flowing therethrough, the wall means also including metallic extended surface elementssecuredin good heat transfer relationship to the tubes and pro,- jecting from the combustion chamber sides of the tubes, high temperature refractory material covering the sides of the tubes toward the combustion chamber face of the wall means, burner means firing the combustion chamber with a whirling motion of the combustion elements, a metallic pressure resistant cylindrical casing enclosing the combustion chamber and spaced outwardly.
  • second hollow cylindrical wall means including similarwall tubes normally having steam flowing therethrough, said second wall means being disposed at a position intermediate the first wall means and the casing and dividing said space into two combustion chamber enveloping spaces
  • first firing means including a device imparting a whirling motion to the gases within the combustion chamber, angularly directed steam nozzles fed by said tubes and directed through the combustion chamber wall so as to augment the whirling motion of thegases within the combustion chamber by their angular jets, and means normallydirecting the flow of a gaseous cooling medium to said spaces and from said spaces to the firing means and to the combustion chamber at distributed positions.
  • wall means defining a combustion chamber of hollow cylindrical shape
  • burner means firing the combustion chamber at one end thereof with a whirling motion of the combustion elements
  • a metallic pressure resistant cylindrical casing enclosing the combustion chamber and spaced outwardly therefrom to provide a.
  • substantially annular space for, av gaseous combustion supportin medium means normally directing a'flow ofgaseous combustion supporting mediumto said space and to the firing means, means forming a combustion chamber outlet at the end of the combustion chamber opposite the firing means, substantiallycircumferentially and helically directed nozzle means distributed over the length of the combustion chamber and extending through its wall and arranged tolclirect jets ofa gaseous cooling, medium substantially helically of the combustion chamber and toward the combustion chamber, gas outlet, means for supplying said, nozzle means with the; gaseous cooling mediumunder pressure, the temperature of said medium suppliedto the nozzle means being substanti lly: le s.
  • combustion chamber wall means being formed with openings distributed over the area of the wall means and directing the gaseous combustion supporting medium from said annular space somewhat helically and toward the combustion chamber outlet.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US15832A 1947-03-21 1948-03-19 Gas turbine combustor having helically directed openings to admit steam and secondary air Expired - Lifetime US2636345A (en)

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GB7846/47A GB622537A (en) 1947-03-21 1947-03-21 Improvements in or relating to furnaces

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Cited By (31)

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US2770097A (en) * 1952-02-14 1956-11-13 William C Walker Cooling systems for engines that utilize heat
US2847825A (en) * 1953-07-31 1958-08-19 Gen Motors Corp Gas turbine thrust augmenter comprising water injection ring
US2916877A (en) * 1954-05-12 1959-12-15 Worthington Corp Pressure fluid generator
US3078672A (en) * 1959-03-28 1963-02-26 Maschf Augsburg Nuernberg Ag Process and apparatus for operating a continuous or intermittent combustion engine
US3359723A (en) * 1965-10-29 1967-12-26 Exxon Research Engineering Co Method of combusting a residual fuel utilizing a two-stage air injection technique and an intermediate steam injection step
US3657884A (en) * 1970-11-20 1972-04-25 Westinghouse Electric Corp Trans-nozzle steam injection gas turbine
US3772881A (en) * 1970-06-04 1973-11-20 Texaco Ag Apparatus for controllable in-situ combustion
US3785146A (en) * 1972-05-01 1974-01-15 Gen Electric Self compensating flow divider for a gas turbine steam injection system
US4074708A (en) * 1976-06-07 1978-02-21 Combustion Engineering, Inc. Burning hydrogen and oxygen to superheat steam
WO1982001214A1 (en) * 1980-10-07 1982-04-15 Foster Miller Ass Thermal enhancement
US4456068A (en) * 1980-10-07 1984-06-26 Foster-Miller Associates, Inc. Process and apparatus for thermal enhancement
US4459101A (en) * 1981-08-28 1984-07-10 Foster-Miller Associates, Inc. Burner systems
DE3545524A1 (de) * 1985-12-20 1987-07-02 Kraftwerk Union Ag Mehrstufenbrennkammer fuer die verbrennung von stickstoffhaltigem gas mit verringerter no(pfeil abwaerts)x(pfeil abwaerts)-emission und verfahren zu ihrem betrieb
US5461854A (en) * 1993-07-07 1995-10-31 Griffin, Jr.; Arthur T. Combustor cooling for gas turbine engines
US5819540A (en) * 1995-03-24 1998-10-13 Massarani; Madhat Rich-quench-lean combustor for use with a fuel having a high vanadium content and jet engine or gas turbine system having such combustors
US6085514A (en) * 1996-12-27 2000-07-11 Abb Alstom Power (Switzerland) Ltd. Method of steam cooling thermally highly loaded units of a gas-turbine group
US6105372A (en) * 1997-09-08 2000-08-22 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor
US6176075B1 (en) 1993-07-07 2001-01-23 Arthur T. Griffin, Jr. Combustor cooling for gas turbine engines
US6389814B2 (en) 1995-06-07 2002-05-21 Clean Energy Systems, Inc. Hydrocarbon combustion power generation system with CO2 sequestration
US6523349B2 (en) 2000-03-22 2003-02-25 Clean Energy Systems, Inc. Clean air engines for transportation and other power applications
US6622470B2 (en) 2000-05-12 2003-09-23 Clean Energy Systems, Inc. Semi-closed brayton cycle gas turbine power systems
US20040065086A1 (en) * 2002-10-02 2004-04-08 Claudio Filippone Small scale hybrid engine (SSHE) utilizing fossil fuels
US20040128975A1 (en) * 2002-11-15 2004-07-08 Fermin Viteri Low pollution power generation system with ion transfer membrane air separation
US20040221581A1 (en) * 2003-03-10 2004-11-11 Fermin Viteri Reheat heat exchanger power generation systems
US20050056020A1 (en) * 2003-08-26 2005-03-17 Honeywell International Inc. Tube cooled combustor
US6868677B2 (en) 2001-05-24 2005-03-22 Clean Energy Systems, Inc. Combined fuel cell and fuel combustion power generation systems
US20050126156A1 (en) * 2001-12-03 2005-06-16 Anderson Roger E. Coal and syngas fueled power generation systems featuring zero atmospheric emissions
US20050241311A1 (en) * 2004-04-16 2005-11-03 Pronske Keith L Zero emissions closed rankine cycle power system
US7574870B2 (en) 2006-07-20 2009-08-18 Claudio Filippone Air-conditioning systems and related methods
US20090235671A1 (en) * 2008-03-19 2009-09-24 Gas Technology Institute Partial oxidation gas turbine cooling
CN102345880A (zh) * 2010-08-03 2012-02-08 通用电气公司 带中心主体冷却系统的燃料喷嘴

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BE507040A (zh) * 1950-11-17
DE931508C (de) * 1952-05-24 1955-08-11 Heinrich Dr-Ing Vorkauf Heizflaeche zur Kuehlung von Gasturbinen-Brennkammern
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US660996A (en) * 1900-06-06 1900-10-30 John Thomas Nicolson Caloric-engine.
GB190426178A (en) * 1904-12-01 1906-03-01 Adolf Vogt Improvements in Apparatus for Producing Combustion Gases under Pressure for use as Motive Power for Driving Turbines and the like, and Means in Combination therewith for Producing a Liquid Jet.
GB190804129A (en) * 1907-02-28 1909-03-24 Louis Jules Jean Baptiste Rond Improvements in or relating to Thermic Engines particularly applicable to Motor Vehicles.
GB190807701A (en) * 1908-02-24 1909-04-07 Louis Jules Jean-Baptiste Rond Improvements in or relating to Apparatus for the Treatment of Compressed Fluid for obtaining Motive Power.
US1237877A (en) * 1916-03-27 1917-08-21 Josiah Dow Generation of pressure.
US1840690A (en) * 1927-11-21 1932-01-12 Roy C Bissell Pressure fluid generator
US1781236A (en) * 1928-04-23 1930-11-11 Lilge Friedrich Whirl burner
US2016921A (en) * 1930-02-19 1935-10-08 Robert H Goddard Means for cooling combustion chambers
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FR963507A (zh) 1950-07-17
GB622537A (en) 1949-05-03

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