GB1130371A - Improvements in boundary wall structures for hot fluid streams - Google Patents

Improvements in boundary wall structures for hot fluid streams

Info

Publication number
GB1130371A
GB1130371A GB42717/64A GB4271764A GB1130371A GB 1130371 A GB1130371 A GB 1130371A GB 42717/64 A GB42717/64 A GB 42717/64A GB 4271764 A GB4271764 A GB 4271764A GB 1130371 A GB1130371 A GB 1130371A
Authority
GB
United Kingdom
Prior art keywords
flow
wall
passage
cooling air
outlet
Prior art date
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
Application number
GB42717/64A
Inventor
Leslie Frederick Richardson
Stephen Downing Barnwell
John Francis Palmer
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB42717/64A priority Critical patent/GB1130371A/en
Priority to US497360A priority patent/US3362470A/en
Publication of GB1130371A publication Critical patent/GB1130371A/en
Expired legal-status Critical Current

Links

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
    • F23R3/02—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
    • F28—HEAT EXCHANGE IN GENERAL
    • F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
    • F28D3/00—Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium flows in a continuous film, or trickles freely, over the conduits
    • 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

Abstract

1,130,371. Gas turbine engine combustion equipment. ROLLS-ROYCE Ltd. Oct. 27, 1965 [Oct. 20, 1964; Aug. 3, 1965], Nos. 42717/64 and 33073/65. Heading F1L. The invention relates to a passage system for cooling a wall which divides a hot fluid-flow from a cooler fluid-flow of higher pressure and is described with reference to combustion equipment of a gas turbine engine. The flow passage extends between an inlet for the cold flow and an outlet to the hot flow and is shaped to direct cold fluid as a film between the wall and the hot flow adjacent thereto, the outlet having an effective flow area not less than that of the inlet. The flow passage includes a chamber which provides a sudden enlargement of the flow area so as to create turbulence in the flow, and downstream of the sudden enlargement a portion of substantially uniform flow area to assist in settling the turbulence and in forming a uniform flow. A member having surfaces lying parallel to the intended direction of flow is disposed in the portion of uniform flow area. Part of the wall 16 of a combustion system flame tube is shown in Fig. 3 the wall being formed with openings 25 for flow of cooling air from the flow 17. Inwardly of the openings 25 is disposed a wall member 28 which forms a flow passage 30, a corrugated member 32 being disposed between the flame tube wall 16 and the downstream end of the wall 28. The flow passage affords a zone of sudden enlargement at 34 downstream of the inlet openings 25, a portion 35 of uniform flow area wherein the turbulence created in the enlargement 34 settles, and an outlet 26, the flow of cooling air along the inner surface of the wall 16 being indicated at 21 and the combustion gas flow within the flame tube at 22. In a second embodiment Fig. 7, the flame tube is formed of tubular sections 40 of increasing diameter in the direction of flow and the cooling fluid passage system is provided in a member 41 which is secured between adjacent sections 40 by welding at 49. The member 41 comprises an outer wall 42 and an inner wall 43 and is formed with a cooling air inlet 25 and cooling air outlet 26. The annular flow path 20 between the walls affords a zone of sudden enlargement at 34 and a region of uniform flow at 35. A web 46 extends between the walls 42, 43, the web being formed with holes 47 therethrough. The passage 48 downstream of the holes 47 is of convergent form.
GB42717/64A 1964-10-20 1964-10-20 Improvements in boundary wall structures for hot fluid streams Expired GB1130371A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB42717/64A GB1130371A (en) 1964-10-20 1964-10-20 Improvements in boundary wall structures for hot fluid streams
US497360A US3362470A (en) 1964-10-20 1965-10-18 Boundary wall structures for hot fluid streams

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB42717/64A GB1130371A (en) 1964-10-20 1964-10-20 Improvements in boundary wall structures for hot fluid streams

Publications (1)

Publication Number Publication Date
GB1130371A true GB1130371A (en) 1968-10-16

Family

ID=10425667

Family Applications (1)

Application Number Title Priority Date Filing Date
GB42717/64A Expired GB1130371A (en) 1964-10-20 1964-10-20 Improvements in boundary wall structures for hot fluid streams

Country Status (2)

Country Link
US (1) US3362470A (en)
GB (1) GB1130371A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2155835A1 (en) * 1971-10-08 1973-05-25 Snecma
US4446693A (en) * 1980-11-08 1984-05-08 Rolls-Royce Limited Wall structure for a combustion chamber
CN111780164A (en) * 2020-06-11 2020-10-16 中国航发湖南动力机械研究所 Flame tube head structure, flame tube and gas turbine engine

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3428114A (en) * 1967-03-27 1969-02-18 Us Interior Method and apparatus for preventing scale formation in heat exchangers
US3899876A (en) * 1968-11-15 1975-08-19 Secr Defence Brit Flame tube for a gas turbine combustion equipment
US3995422A (en) * 1975-05-21 1976-12-07 General Electric Company Combustor liner structure

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2658337A (en) * 1947-12-23 1953-11-10 Lucas Ltd Joseph Combustion chamber for prime movers
US2770097A (en) * 1952-02-14 1956-11-13 William C Walker Cooling systems for engines that utilize heat
US2785878A (en) * 1953-09-16 1957-03-19 Earl W Conrad Porous walled conduit for fluid cooling
US2775094A (en) * 1953-12-03 1956-12-25 Gen Electric End cap for fluid fuel combustor
US2884759A (en) * 1956-04-25 1959-05-05 Curtiss Wright Corp Combustion chamber construction
US2916878A (en) * 1958-04-03 1959-12-15 Gen Electric Air-directing vane structure for fluid fuel combustor

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2155835A1 (en) * 1971-10-08 1973-05-25 Snecma
US4446693A (en) * 1980-11-08 1984-05-08 Rolls-Royce Limited Wall structure for a combustion chamber
CN111780164A (en) * 2020-06-11 2020-10-16 中国航发湖南动力机械研究所 Flame tube head structure, flame tube and gas turbine engine
CN111780164B (en) * 2020-06-11 2022-05-17 中国航发湖南动力机械研究所 Flame tube head structure, flame tube and gas turbine engine

Also Published As

Publication number Publication date
US3362470A (en) 1968-01-09

Similar Documents

Publication Publication Date Title
US2458497A (en) Combustion chamber
US3643431A (en) Flow control devices
KR870009116A (en) Gas turbine combustor
GB1519604A (en) Jet engine cooled varable area exhaust nozzle
GB1314666A (en) Flame tubes for combustion chambers for gas turbine engines
US3820324A (en) Flame tubes for gas turbine engines
GB1278590A (en) Combustion chambers for gas turbine engines
US2645082A (en) Surface gap igniter plug for gas turbines
US2458066A (en) Combustion chamber
GB1130371A (en) Improvements in boundary wall structures for hot fluid streams
US2269333A (en) Fuel burner
GB1138679A (en) Wall element for combustion chambers
GB1114823A (en) Improvements in or relating to combustion chambers
GB836117A (en) Improvements in or relating to combustion equipment for gas-turbine engines
GB1060095A (en) Improvements relating to the flow of a cooling fluid
US3207597A (en) Method of adding a liquid fuel to the air blast in a shaft furnace or specifically in a blast furnace
US1075742A (en) Burner.
GB1537037A (en) Burners for fluid fuels
GB598947A (en) Improvements in or relating to apparatus for mixing fluids
US2655992A (en) Mixer for gas burners
GB887639A (en) Combustion equipment for a gas turbine engine
GB1016020A (en) Device for reducing the noise of fluid flow
GB1283827A (en) Improvements in or relating to combustion apparatus
GB1235914A (en) Improvements in liquid cooled rocket combustion chambers
GB1060097A (en) Improvements relating to the flow of a cooling fluid