US2494821A - Means for supporting the nozzles of the combustion chambers of internal-combustion turbines - Google Patents

Means for supporting the nozzles of the combustion chambers of internal-combustion turbines Download PDF

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Publication number
US2494821A
US2494821A US733912A US73391247A US2494821A US 2494821 A US2494821 A US 2494821A US 733912 A US733912 A US 733912A US 73391247 A US73391247 A US 73391247A US 2494821 A US2494821 A US 2494821A
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US
United States
Prior art keywords
ring
combustion
turbine
casing
nozzles
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Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
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US733912A
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English (en)
Inventor
Lombard Adrian Albert
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Rolls Royce PLC
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Rolls Royce PLC
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Publication date
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Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
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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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • 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

Definitions

  • nozzles which are circular at their forward or inlet ends-where they receive the combustion products from the combustion equipment-and substantially rectangular at their rear or outlet ends-where they direct the combustion products on to the nozzle guide vane assembly; the outlet ends of the nozzles were arranged side by side to form a complete annular ring corresponding to the annulus oi the nozzle guide vane assembly.
  • the nozzles were welded together along radially abutting edges at their outlet ends and further the inner and outer diametral edges at the outlet ends were welded to inner and outer support rings.
  • the object of the present invention is to provide a construction in which the nozzles and the nozzle guide vanes which-operate at high temperature are relieved of structural loading and which permits these components being sosupported that they can expand freely within the assembly.
  • an internalcombustion turbine of the above kind is provided with an apertured ring to receive and support the outlet ends of the combustion chambers, the ring being secured to the intermediate casing and to 2 the outer ring of the nozzle guide vane assembly so that structural loads are transmitted from one to the other solely through the ring.
  • Figure 1 is a side elevation of a jet propulsion gas turbine engine for an aeroplane incorporating a turbine in accordance with this invention
  • Figure 3 is a similar view to Figure 2 showing to a greater scale certain details of construction of the invention.
  • the jet-propulsion gasturbine engine comprises a compressor casing 5 to house a centrifugal impeller, which is driven by a single-stage turbine generally indicated at 8.
  • a plurality of combustion chambers 1 receive air from the compressor 5 by ducts 5a, and liquid fuel is burnt in these chambers.
  • the products of combustion are delivered to turbine 6 and then pass to atmosphere by way of exhaust assembly 8.
  • the exhaust gases being directed rearwardly by the exhaust assembly relative to the direction of flight of the aeroplane provide reaction propulsion.
  • a turbine shaft Ill supports the turbine disc .II which carries blades l2.
  • the shaft Ill is supported by a roller bearing, generally indicated at l3, carried by a structure H extending from an intermediate casing I5 which is bolted to the compressor casing 5.
  • the turbine rotor assembly is supported from the compressor casing, the intermediate casing I5 and extension casing l4 providing a backbone structure for the engine.
  • the fixed-blade assembly is also shown in Figure 3 and it will be observed that a ring 20a, forming one part of a labyrinth seal, is bolted to the inner ring 20, which in turn is bolted at 22 to a tubular member 23.
  • the outer stator blade ring 19 is secured by studs, as at 24, to an annular ring 25 that forms part of the nozzle box structure.
  • the nozzle boxes 33 which are fabricated sheet shaft to extend irom the compressor toward the turbine, an exhaust unit supported from the turbine casing on the side thereof remote irom the compressor, an intermediate casing surrounding the shall; within the ring of combustion chambers and secured to the compressor casing to extend towards the turbine, a ring-like casing member having formed therein a plurality of circumferentially-spaced apertures one for each combustion chamber to receive andsupport its outlet end, said ring-like casing member being connected to the intermediate casing and to the outer periphery oithe turbine casing to transmit structural loads therebetween, and a plurality of nozzle-boxes one for each combustion chamberextending from the outlets of the combustion chambers to deliver the working fluid from the combustion chambers to the turbine, the walls of the nozzle-boxes being spaced from the ring-like casing member so that the latter is out 01 direct contact with the flow of working fluid through said nozzle boxes.
  • the nozzle boxes 33 are of substantially trapezoidal form (as shown in Figure 5) so that when assembled they form an annular, gas duct leading to the nozzle guide vanes 2
  • the exit ends ( Figure 3) are supported between casing 23 and an intermediate ring 31, disposed between the supporting ring is and ring 25.
  • nozzle boxes 33 serves not only their normal function of directing the combustion productsfrom the flame tube 1b to the nozzle guide vanes but also to prevent'the gases coming into contact with the housing structure. The latter not being subjected to high temperature does not have its structural strength im-' paired.
  • a sheet metal collector. ring 40 is attached to the nozzle box structure by studs 2'! and 24 ( Figures 2 and 3).
  • the purpose of this ring is to define, with casing 25, an annular space to receive cooling air which is conveyed thereto fromthe interior of thecasing 23 by pipes (not shown).
  • a gas-turbine engine as claimed in claim 1 wherein said turbine casing comprises a stationary shroud for the turbine rotor, an outer ring secured directly to said shroud, an inner ring located within and radially spaced from the outer ring, and a series of guide-blades supported between the inner and outer rings, wherein said apertured ring-like casing member is of dished form, extends outwardly from the intermediate casing and has its concave face towards the turbine, and wherein the outer edge of said aper-- tured ring-like casing member is connected to the outer ring by a first tubular member surrounding said nozzle-boxes and the inner edge of said apertured ring-like casing member is connected to the inner-ring by a second tubular member disposed radially inside the nozzle-boxes said apertured ring-like casing member and said first and second tubular members together forming a chamber enclosing the nozzle-boxes.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US733912A 1946-03-25 1947-03-11 Means for supporting the nozzles of the combustion chambers of internal-combustion turbines Expired - Lifetime US2494821A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB9203/46A GB610113A (en) 1946-03-25 1946-03-25 Improvements in or relating to gas-turbine engines

Publications (1)

Publication Number Publication Date
US2494821A true US2494821A (en) 1950-01-17

Family

ID=9867397

Family Applications (1)

Application Number Title Priority Date Filing Date
US733912A Expired - Lifetime US2494821A (en) 1946-03-25 1947-03-11 Means for supporting the nozzles of the combustion chambers of internal-combustion turbines

Country Status (5)

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US (1) US2494821A (en))
BE (1) BE487120A (en))
CH (1) CH258674A (en))
FR (1) FR943932A (en))
GB (1) GB610113A (en))

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2594808A (en) * 1947-03-14 1952-04-29 Rolls Royce Means for supporting the nozzles of the combustion chambers of internal-combustion turbines
US2608057A (en) * 1949-12-24 1952-08-26 A V Roe Canada Ltd Gas turbine nozzle box
US2609176A (en) * 1950-01-21 1952-09-02 A V Roe Canada Ltd Turbine nozzle guide vane construction
US2654566A (en) * 1950-02-11 1953-10-06 A V Roe Canada Ltd Turbine nozzle guide vane construction
US2699040A (en) * 1950-05-23 1955-01-11 Gen Motors Corp Detachable combustion chamber for gas turbines
US2702454A (en) * 1951-06-07 1955-02-22 United Aircraft Corp Transition piece providing a connection between the combustion chambers and the turbine nozzle in gas turbine power plants
US2711074A (en) * 1944-06-22 1955-06-21 Gen Electric Aft frame and rotor structure for combustion gas turbine
US2747367A (en) * 1950-03-21 1956-05-29 United Aircraft Corp Gas turbine power plant supporting structure
US2763462A (en) * 1950-01-11 1956-09-18 Gen Motors Corp Turbine casing construction
US2780174A (en) * 1951-03-19 1957-02-05 Solar Aircraft Co Pump and power plant assembly
US2789787A (en) * 1949-10-22 1957-04-23 Svenska Turbinfab Ab Guide blade device for steam or gas turbines
US2825285A (en) * 1953-12-28 1958-03-04 Belton A Copp Centrifugal pump with discharge manifold
US2839894A (en) * 1952-12-31 1958-06-24 Gen Motors Corp Supporting arrangement for a gas turbine combustion chamber
US2848191A (en) * 1951-11-03 1958-08-19 A V Roe Canada Ltd Nozzle box
US2984454A (en) * 1957-08-22 1961-05-16 United Aircraft Corp Stator units
US4573315A (en) * 1984-05-15 1986-03-04 A/S Kongsberg Vapenfabrikk Low pressure loss, convectively gas-cooled inlet manifold for high temperature radial turbine
US6116013A (en) * 1998-01-02 2000-09-12 Siemens Westinghouse Power Corporation Bolted gas turbine combustor transition coupling
US20110173990A1 (en) * 2010-01-20 2011-07-21 Rolls-Royce Deutschland Ltd & Co Kg Intermediate casing for a gas-turbine engine
US20140311121A1 (en) * 2012-10-12 2014-10-23 United Technologies Corporation Pulse detonation engine having a scroll ejector attenuator
US9470422B2 (en) 2013-10-22 2016-10-18 Siemens Energy, Inc. Gas turbine structural mounting arrangement between combustion gas duct annular chamber and turbine vane carrier
US9810434B2 (en) * 2016-01-21 2017-11-07 Siemens Energy, Inc. Transition duct system with arcuate ceramic liner for delivering hot-temperature gases in a combustion turbine engine
CN115288804A (zh) * 2022-10-10 2022-11-04 中国航发四川燃气涡轮研究院 一种鸟类骨架仿生式承力结构及其设计方法

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1218800B (de) * 1961-04-25 1966-06-08 M A N Turbo Ges Mit Beschraenk Gasturbine, insbesondere Kleingasturbine
GB0618991D0 (en) 2006-09-27 2006-11-08 Rolls Royce Plc A component for a gas turbine engine
US10465642B2 (en) 2017-03-27 2019-11-05 Kohler Co. Carburetor drain
CN113154456B (zh) * 2021-04-15 2022-06-21 中国航发湖南动力机械研究所 回流燃烧室机匣头部结构及其制造方法和发动机燃烧室

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB579331A (en) * 1943-07-13 1946-07-31 Francis Robert Bell Improvements in combustion chambers for power-gas-generators, internal-combustion turbines and the like
GB588082A (en) * 1941-08-25 1947-05-14 Power Jets Ltd Improvements relating to engines
US2432359A (en) * 1947-12-09 Internal-combustion turbine power

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2432359A (en) * 1947-12-09 Internal-combustion turbine power
GB588082A (en) * 1941-08-25 1947-05-14 Power Jets Ltd Improvements relating to engines
GB579331A (en) * 1943-07-13 1946-07-31 Francis Robert Bell Improvements in combustion chambers for power-gas-generators, internal-combustion turbines and the like

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2711074A (en) * 1944-06-22 1955-06-21 Gen Electric Aft frame and rotor structure for combustion gas turbine
US2594808A (en) * 1947-03-14 1952-04-29 Rolls Royce Means for supporting the nozzles of the combustion chambers of internal-combustion turbines
US2789787A (en) * 1949-10-22 1957-04-23 Svenska Turbinfab Ab Guide blade device for steam or gas turbines
US2608057A (en) * 1949-12-24 1952-08-26 A V Roe Canada Ltd Gas turbine nozzle box
US2763462A (en) * 1950-01-11 1956-09-18 Gen Motors Corp Turbine casing construction
US2609176A (en) * 1950-01-21 1952-09-02 A V Roe Canada Ltd Turbine nozzle guide vane construction
US2654566A (en) * 1950-02-11 1953-10-06 A V Roe Canada Ltd Turbine nozzle guide vane construction
US2747367A (en) * 1950-03-21 1956-05-29 United Aircraft Corp Gas turbine power plant supporting structure
US2699040A (en) * 1950-05-23 1955-01-11 Gen Motors Corp Detachable combustion chamber for gas turbines
US2780174A (en) * 1951-03-19 1957-02-05 Solar Aircraft Co Pump and power plant assembly
US2702454A (en) * 1951-06-07 1955-02-22 United Aircraft Corp Transition piece providing a connection between the combustion chambers and the turbine nozzle in gas turbine power plants
US2848191A (en) * 1951-11-03 1958-08-19 A V Roe Canada Ltd Nozzle box
US2839894A (en) * 1952-12-31 1958-06-24 Gen Motors Corp Supporting arrangement for a gas turbine combustion chamber
US2825285A (en) * 1953-12-28 1958-03-04 Belton A Copp Centrifugal pump with discharge manifold
US2984454A (en) * 1957-08-22 1961-05-16 United Aircraft Corp Stator units
US4573315A (en) * 1984-05-15 1986-03-04 A/S Kongsberg Vapenfabrikk Low pressure loss, convectively gas-cooled inlet manifold for high temperature radial turbine
US6116013A (en) * 1998-01-02 2000-09-12 Siemens Westinghouse Power Corporation Bolted gas turbine combustor transition coupling
US20110173990A1 (en) * 2010-01-20 2011-07-21 Rolls-Royce Deutschland Ltd & Co Kg Intermediate casing for a gas-turbine engine
US8857193B2 (en) 2010-01-20 2014-10-14 Rolls-Royce Deutschland Ltd & Co Kg Intermediate casing for a gas-turbine engine
US20140311121A1 (en) * 2012-10-12 2014-10-23 United Technologies Corporation Pulse detonation engine having a scroll ejector attenuator
US9021783B2 (en) * 2012-10-12 2015-05-05 United Technologies Corporation Pulse detonation engine having a scroll ejector attenuator
US9470422B2 (en) 2013-10-22 2016-10-18 Siemens Energy, Inc. Gas turbine structural mounting arrangement between combustion gas duct annular chamber and turbine vane carrier
US9810434B2 (en) * 2016-01-21 2017-11-07 Siemens Energy, Inc. Transition duct system with arcuate ceramic liner for delivering hot-temperature gases in a combustion turbine engine
CN115288804A (zh) * 2022-10-10 2022-11-04 中国航发四川燃气涡轮研究院 一种鸟类骨架仿生式承力结构及其设计方法

Also Published As

Publication number Publication date
FR943932A (fr) 1949-03-22
CH258674A (de) 1948-12-15
GB610113A (en) 1948-10-12
BE487120A (en))

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