GB1346600A - Flame tubes for gas turbine engines - Google Patents

Flame tubes for gas turbine engines

Info

Publication number
GB1346600A
GB1346600A GB1346600DA GB1346600A GB 1346600 A GB1346600 A GB 1346600A GB 1346600D A GB1346600D A GB 1346600DA GB 1346600 A GB1346600 A GB 1346600A
Authority
GB
United Kingdom
Prior art keywords
tube
clamping
clamping means
differential thermal
members
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
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.)
ZF International UK Ltd
Original Assignee
Lucas Industries Ltd
Joseph Lucas Industries Ltd
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 Lucas Industries Ltd, Joseph Lucas Industries Ltd filed Critical Lucas Industries Ltd
Publication of GB1346600A publication Critical patent/GB1346600A/en
Expired legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/007Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Ceramic Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Compositions Of Oxide Ceramics (AREA)

Abstract

1346600 Gas turbine combustion chambers JOSEPH LUCAS (INDUSTRIES) Ltd 2 Aug 1971 [12 June 1970] 28539/70 Heading F1L A flame tube for a gas turbine engine comprises a first tube member 45, Fig. 4, of ceramic material secured to a second tube member in axially-spaced concentric relationship by clamping, means which compensates for differential thermal expansion between the clamping means and at least one of the tube members. The clamping means has frusto-conical surfaces on metal members 51, 52 and 54, 55 which co-operate with complementary surfaces on ceramic tube members 45, 46, the included angle of the surfaces being such that substantially constant clamping force is maintained at the co-operating surfaces during differential thermal expansion. A ceramic air baffle 57 is similarly secured by clamping means 58, and is located in the inlet end of the flame tube by a system of relatively slidable rods 60 and tubes 59. The flame tube is attached by lugs 66 to a structure 62 defining with a cylinder 70 of expanded metal mesh, an annular space 63 through which air is introduced. The air flows into the flame tube through the annular gap at the periphery of baffle 57, the axial gap between the tube members 45, 46, and dilution holes 56. In Fig. 3 (not shown), the upstream tube member is composed of several axially-stacked frusto-conical ceramic rings (32) clamped together by differential thermal expansion compensating clamping means which also couples the two tube members together in axially-spaced relationship. In Fig.1, each tube member 10, 11 comprises four quadrants 14 and and 19 respectively, each quadrant having radial lugs (15), Fig.2 (not shown) at their circumferential ends by which they are secured together by clamping means 16 and 20. The latter have clamping elements 16a, 16b and 20a, 20b for this purpose, the co-operating surfaces of these elements and the lugs (15) being tapered radially inwardly to compensate for differential thermal expansions. Packing material may be located between the co-operating clamping surfaces in all arrangements described.
GB1346600D 1970-06-12 1970-06-12 Flame tubes for gas turbine engines Expired GB1346600A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2853970 1970-06-12

Publications (1)

Publication Number Publication Date
GB1346600A true GB1346600A (en) 1974-02-13

Family

ID=10277239

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1346600D Expired GB1346600A (en) 1970-06-12 1970-06-12 Flame tubes for gas turbine engines

Country Status (1)

Country Link
GB (1) GB1346600A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2552860A1 (en) * 1983-10-03 1985-04-05 Gen Electric COMBUSTION CHAMBER SHIRT
US5319922A (en) * 1992-12-04 1994-06-14 General Electric Company Aircraft gas turbine engine backbone deflection control
WO2016124348A1 (en) * 2015-02-06 2016-08-11 Siemens Aktiengesellschaft Annular combustion chamber with bypass segment
CN113333549A (en) * 2021-06-21 2021-09-03 西安远航真空钎焊技术有限公司 Method for processing front ring of flame tube of gas turbine

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2552860A1 (en) * 1983-10-03 1985-04-05 Gen Electric COMBUSTION CHAMBER SHIRT
US5319922A (en) * 1992-12-04 1994-06-14 General Electric Company Aircraft gas turbine engine backbone deflection control
WO2016124348A1 (en) * 2015-02-06 2016-08-11 Siemens Aktiengesellschaft Annular combustion chamber with bypass segment
CN113333549A (en) * 2021-06-21 2021-09-03 西安远航真空钎焊技术有限公司 Method for processing front ring of flame tube of gas turbine
CN113333549B (en) * 2021-06-21 2022-09-06 西安远航真空钎焊技术有限公司 Method for machining front ring of flame tube of gas turbine

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Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee