[go: up one dir, main page]

GB2001692A - Honeycomb structures: gas turbines - Google Patents

Honeycomb structures: gas turbines

Info

Publication number
GB2001692A
GB2001692A GB7828646A GB7828646A GB2001692A GB 2001692 A GB2001692 A GB 2001692A GB 7828646 A GB7828646 A GB 7828646A GB 7828646 A GB7828646 A GB 7828646A GB 2001692 A GB2001692 A GB 2001692A
Authority
GB
United Kingdom
Prior art keywords
gas turbines
honeycomb structures
strips
honeycomb
abutting areas
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.)
Granted
Application number
GB7828646A
Other versions
GB2001692B (en
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 GB7828646A priority Critical patent/GB2001692B/en
Publication of GB2001692A publication Critical patent/GB2001692A/en
Application granted granted Critical
Publication of GB2001692B publication Critical patent/GB2001692B/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/127—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with a deformable or crushable structure, e.g. honeycomb
    • 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
    • F05D2250/28—Three-dimensional patterned
    • F05D2250/283—Three-dimensional patterned honeycomb

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

A honeycomb structure for use in gas turbine engines is made from a plurality of shaped strips (12a, b, etc.) connected together to form the cells, the structure being brazed to a backing sheet 15. Non-abutting areas are formed between the connecting faces (e.g. 14a, 14b) of adjacent strips to prevent capillary flow of molten braze metal to the surface of the honeycomb. The non-abutting areas may be at the top surface, as fig. 1, or intermediate the edges of the strips (fig. 4), <IMAGE>
GB7828646A 1977-07-29 1978-07-03 Honeycomb structures Expired GB2001692B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB7828646A GB2001692B (en) 1977-07-29 1978-07-03 Honeycomb structures

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB3207177 1977-07-29
GB7828646A GB2001692B (en) 1977-07-29 1978-07-03 Honeycomb structures

Publications (2)

Publication Number Publication Date
GB2001692A true GB2001692A (en) 1979-02-07
GB2001692B GB2001692B (en) 1982-01-27

Family

ID=26261198

Family Applications (1)

Application Number Title Priority Date Filing Date
GB7828646A Expired GB2001692B (en) 1977-07-29 1978-07-03 Honeycomb structures

Country Status (1)

Country Link
GB (1) GB2001692B (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0081010A3 (en) * 1981-08-10 1983-08-03 George T. Straza Interrupted cell honeycomb structure
GB2128261A (en) * 1982-09-30 1984-04-26 John R Plautz Honeycomb structure, e.g. for a turbine shroud
US4449714A (en) * 1983-03-22 1984-05-22 Gulf & Western Industries, Inc. Turbine engine seal and method for repair thereof
FR2539479A1 (en) * 1983-01-13 1984-07-20 Campbell James HONEYCOMB JOINT STRUCTURE
US7105219B2 (en) 2004-05-27 2006-09-12 Mitsubishi Heavy Industries, Ltd. Brazing construction and method of brazing an abradable sealing material
EP3135869A1 (en) * 2015-08-25 2017-03-01 Rolls-Royce Deutschland Ltd & Co KG Sealing element for a turbomachine, corresponding turbomachine and manufacturing process

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0081010A3 (en) * 1981-08-10 1983-08-03 George T. Straza Interrupted cell honeycomb structure
GB2128261A (en) * 1982-09-30 1984-04-26 John R Plautz Honeycomb structure, e.g. for a turbine shroud
FR2539479A1 (en) * 1983-01-13 1984-07-20 Campbell James HONEYCOMB JOINT STRUCTURE
US4449714A (en) * 1983-03-22 1984-05-22 Gulf & Western Industries, Inc. Turbine engine seal and method for repair thereof
EP0119343A1 (en) * 1983-03-22 1984-09-26 Gulf And Western Industries, Inc. Turbine engine seal and method for repair thereof
US7105219B2 (en) 2004-05-27 2006-09-12 Mitsubishi Heavy Industries, Ltd. Brazing construction and method of brazing an abradable sealing material
EP3135869A1 (en) * 2015-08-25 2017-03-01 Rolls-Royce Deutschland Ltd & Co KG Sealing element for a turbomachine, corresponding turbomachine and manufacturing process
US10480340B2 (en) 2015-08-25 2019-11-19 Rolls-Royce Deutschland Ltd & Co Kg Sealing element for a turbo-machine, turbo-machine comprising a sealing element and method for manufacturing a sealing element

Also Published As

Publication number Publication date
GB2001692B (en) 1982-01-27

Similar Documents

Publication Publication Date Title
IT1076328B (en) BLADE OR SHOVEL FOR A GAS TURBINE ENGINE
GB2096525B (en) Manufacturing gas turbine engine blades
GB2019947B (en) Gas turbine engine combustor assembly
IT7924987A0 (en) COMPOUND CERAMIC BLADE FOR GAS TURBINE.
IT1171753B (en) JOINT OF A CERAMIC ROTARY BUILDING ELEMENT WITH A METALLIC ROTARY BUILDING ELEMENT FOR FLUID-DYNAMIC MACHINES, ESPECIALLY GAS TURBINE ENGINES
IT1137783B (en) HEAT EXCHANGER INTEGRATED WITH THE STATIC CASE OF A GAS TURBINE
GB2001692A (en) Honeycomb structures: gas turbines
IT8521926A0 (en) ADJUSTABLE EXHAUST NOZZLE FOR A GAS TURBINE ENGINE.
IT8020073A0 (en) METHOD FOR DIFFUSION BONDING A DOUBLE SHEET COATING TO SUPER ALLOY SUBSTRATES.
AR228902A1 (en) PROCEDURE AND BURNER TO HEAT THE SURFACE OF A SUBSTRATE THROUGH A HOT GAS JET
JPS5420207A (en) Construction for preventing dust of axial flow turbine
FR2400430A1 (en) Honeycombed gas turbine drive - incorporates metal strips forming cells, soldered to metal carrier sheet
DE3585231D1 (en) GAS TURBINE ENGINE.
JPS5582231A (en) Gas turbine engine combustor
DE3577118D1 (en) GAS TURBINE WITH INTERMITTENT COMBUSTION.
AR218023A1 (en) PROCEDURE FOR THE PREPARATION OF ENZYME ALPHA-AMYLASE STABLE TO HEAT AND ACIDS AND PROCEDURE TO CONVERT STARCH TO A STARCH HYDROLYZATE, THROUGH THE ENZYME SO OBTAINED
JPS5420214A (en) Exhaust gas supercharging turbine
GB2001416A (en) Heat insulation
JPS5634057A (en) Solar heat collector
IT1158276B (en) COMBUSTOR FOR IMPROVED COOLING TURBINES OF THE WALLS
IT1122756B (en) FUEL LIMITER FOR COMBUSTION TURBINES
JPS5437952A (en) Manufacturing method of heat exchanger
JPS5535808A (en) Plate type heat exchanger
ES238683U (en) Shell-like structure for hulls or other self-supporting surfaces
IT8223079A0 (en) COMBUSTION TURBINE COMBUSTOR HAVING AN IMPROVED HEAVY OIL FUEL PREPARATION AREA.

Legal Events

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