GB1212593A - Improvements relating to rotary large diameter gas seals - Google Patents

Improvements relating to rotary large diameter gas seals

Info

Publication number
GB1212593A
GB1212593A GB395468A GB395468A GB1212593A GB 1212593 A GB1212593 A GB 1212593A GB 395468 A GB395468 A GB 395468A GB 395468 A GB395468 A GB 395468A GB 1212593 A GB1212593 A GB 1212593A
Authority
GB
United Kingdom
Prior art keywords
channel
metal
container
engine
flange
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
GB395468A
Inventor
John Wotton
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.)
British Aircraft Corp Ltd
Original Assignee
British Aircraft Corp 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 British Aircraft Corp Ltd filed Critical British Aircraft Corp Ltd
Priority to GB395468A priority Critical patent/GB1212593A/en
Priority to FR6901320A priority patent/FR2000730A1/fr
Publication of GB1212593A publication Critical patent/GB1212593A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
    • F02C3/067—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages having counter-rotating rotors
    • 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
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/062—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with aft fan
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/16—Sealings between relatively-moving surfaces
    • F16J15/40—Sealings between relatively-moving surfaces by means of fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/16—Sealings between relatively-moving surfaces
    • F16J15/40—Sealings between relatively-moving surfaces by means of fluid
    • F16J15/403—Sealings between relatively-moving surfaces by means of fluid by changing the state of matter
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/16—Sealings between relatively-moving surfaces
    • F16J15/40—Sealings between relatively-moving surfaces by means of fluid
    • F16J15/42—Sealings between relatively-moving surfaces by means of fluid kept in sealing position by centrifugal force

Abstract

1,212,593. Jet propulsion plant; turbines. BRITISH AIRCRAFT CORP. Ltd. Jan. 14, 1969 [Jan. 25, 1968], No.3954/68. Headings F1J and F1T. [Also in Division F2] A seal between two coaxial parts, one being stationary and the other rotatable (e.g. a seal for preventing the escape of gas through a gap 15 in a gas turbine jet propulsion engine) comprises an inwardly-facing channel 6 on the stationary part, a flange 13 on the rotatable part extending normal to the axis of rotation and into the channel, a container 7 including a heater 12 for supplying the metal gallium 14 in a liquid state to the channel at a point 9 closer to the rotational axis than the outer diameter of the flange, and means 10 for applying pressure to the container upon rotation of the parts so that upon rotation some of the liquid is expelled into the channel and on stopping the rotation the expelled liquid is returned into the container. The gap 15 is between the combustion chambers 5 and a rotary shroud 2a carrying ducted fan blades 1. Before the engine is started the heater 12 is used to melt the metal. The engine is then rotated and-pressure is transmitted to the container 7 via the duct 10 to transfer the liquid metal 14 by way of a duct 8 into the channel 6 where it is centrifuged to take up the position shown in Fig. 2. As the engine speed increases the gas pressure at the gap 15 displaces the level of the metal in one of the legs of the channel as shown in Fig. 1A such that the centrifugal force exerted by the displaced metal balances the pressure exerted by the gas. Following engine shut down, the metal returns to the container 7 via mouth 9 and duct 8 to solidify. Blades 13a, 13b or scollops may be provided on the flanks of the flange 13 and retaining lips 6a, 6b may be provided on the channel. The forces acting axially on the flange 13 due to unequal levels in the channel during operation are opposed to the thrust of the fan blades 1.
GB395468A 1968-01-25 1968-01-25 Improvements relating to rotary large diameter gas seals Expired GB1212593A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB395468A GB1212593A (en) 1968-01-25 1968-01-25 Improvements relating to rotary large diameter gas seals
FR6901320A FR2000730A1 (en) 1968-01-25 1969-01-24

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB395468A GB1212593A (en) 1968-01-25 1968-01-25 Improvements relating to rotary large diameter gas seals

Publications (1)

Publication Number Publication Date
GB1212593A true GB1212593A (en) 1970-11-18

Family

ID=9768026

Family Applications (1)

Application Number Title Priority Date Filing Date
GB395468A Expired GB1212593A (en) 1968-01-25 1968-01-25 Improvements relating to rotary large diameter gas seals

Country Status (2)

Country Link
FR (1) FR2000730A1 (en)
GB (1) GB1212593A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2174762B (en) * 1985-05-01 1990-04-04 Gen Electric Counter rotation power turbine
EP0931962A3 (en) * 1998-01-27 2000-03-22 Rolls-Royce Plc Hydraulic seal
DE19916803A1 (en) * 1999-04-14 2000-10-19 Rolls Royce Deutschland Hydraulic sealing arrangement, in particular on a gas turbine
EP2740976A1 (en) * 2012-12-06 2014-06-11 Rolls-Royce plc A hydraulic seal arrangement
US9133939B2 (en) 2008-10-14 2015-09-15 Rolls-Royce Plc Seal
EP3037622A1 (en) * 2014-12-24 2016-06-29 United Technologies Corporation A turbine engine with guide vanes forward of its fan blades
FR3060061A1 (en) * 2016-12-08 2018-06-15 Safran Aircraft Engines FREE TURBINE TURBINE ENGINE FOR AIRCRAFT

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2174762B (en) * 1985-05-01 1990-04-04 Gen Electric Counter rotation power turbine
EP0931962A3 (en) * 1998-01-27 2000-03-22 Rolls-Royce Plc Hydraulic seal
US6164658A (en) * 1998-01-27 2000-12-26 Rolls-Royce Plc Hydraulic seal
DE19916803A1 (en) * 1999-04-14 2000-10-19 Rolls Royce Deutschland Hydraulic sealing arrangement, in particular on a gas turbine
US6568688B1 (en) 1999-04-14 2003-05-27 Rolls-Royce Deutschland Ltd & Co Kg Hydraulic seal arrangement, more particularly on a gas turbine
US9133939B2 (en) 2008-10-14 2015-09-15 Rolls-Royce Plc Seal
EP2740976A1 (en) * 2012-12-06 2014-06-11 Rolls-Royce plc A hydraulic seal arrangement
US9157532B2 (en) 2012-12-06 2015-10-13 Rolls-Royce Plc Hydraulic seal arrangement
EP3037622A1 (en) * 2014-12-24 2016-06-29 United Technologies Corporation A turbine engine with guide vanes forward of its fan blades
US10711631B2 (en) 2014-12-24 2020-07-14 Raytheon Technologies Corporation Turbine engine with guide vanes forward of its fan blades
FR3060061A1 (en) * 2016-12-08 2018-06-15 Safran Aircraft Engines FREE TURBINE TURBINE ENGINE FOR AIRCRAFT

Also Published As

Publication number Publication date
FR2000730A1 (en) 1969-09-12

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Legal Events

Date Code Title Description
CSNS Application of which complete specification have been accepted and published, but patent is not sealed