GB998755A - Improvements in or relating to combustion equipment - Google Patents

Improvements in or relating to combustion equipment

Info

Publication number
GB998755A
GB998755A GB19120/64A GB1912064A GB998755A GB 998755 A GB998755 A GB 998755A GB 19120/64 A GB19120/64 A GB 19120/64A GB 1912064 A GB1912064 A GB 1912064A GB 998755 A GB998755 A GB 998755A
Authority
GB
United Kingdom
Prior art keywords
connecting member
upstream
annular
downstream
fluted
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
GB19120/64A
Inventor
Frank Henry Stark
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 GB19120/64A priority Critical patent/GB998755A/en
Publication of GB998755A publication Critical patent/GB998755A/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
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

998,755. Gas turbine and like combustion chambers. ROLLS-ROYCE Ltd. May 7, 1964, No. 19120/64. Heading F1L. A gas turbine or ramjet engine combustion chamber flame tube comprises two axially consecutive wall members, the upstream end of the downstream wall member being radially outwardly spaced from the downstream end of the upstream wall member to define an annular space therewith within which is disposed an annular connecting member interconnecting the wall members, the upstream and downstream ends being fluted and the connecting member being of smooth contour, the radially outer and inner surfaces of consecutive peripheral portions of the connecting member being connected to the fluted upstream and downstream ends respectively and dividing the annular space into individual ducts overlapping one another circumferentially. A gas turbine engine flame tube 12 comprises cylindrical sections 13, 14 joined by an annular connecting member 16. The downstream end of section 13 and the upstream end of section 14 are axially aligned and fluted at 13a, 13b and 14a, 14b respectively, flutes 13b, 14a being welded to connecting member 16 to form cooling air passages 20, 21 overlapping circumferentially at "x". The invention is applicable also to annular flame tubes and flame tubes of non-circular cross section.
GB19120/64A 1964-05-07 1964-05-07 Improvements in or relating to combustion equipment Expired GB998755A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB19120/64A GB998755A (en) 1964-05-07 1964-05-07 Improvements in or relating to combustion equipment

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB19120/64A GB998755A (en) 1964-05-07 1964-05-07 Improvements in or relating to combustion equipment

Publications (1)

Publication Number Publication Date
GB998755A true GB998755A (en) 1965-07-21

Family

ID=10124085

Family Applications (1)

Application Number Title Priority Date Filing Date
GB19120/64A Expired GB998755A (en) 1964-05-07 1964-05-07 Improvements in or relating to combustion equipment

Country Status (1)

Country Link
GB (1) GB998755A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3702058A (en) * 1971-01-13 1972-11-07 Westinghouse Electric Corp Double wall combustion chamber

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3702058A (en) * 1971-01-13 1972-11-07 Westinghouse Electric Corp Double wall combustion chamber

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