EP0795682A1 - Anneau de protection pour une turbosoufflante - Google Patents

Anneau de protection pour une turbosoufflante Download PDF

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Publication number
EP0795682A1
EP0795682A1 EP97300729A EP97300729A EP0795682A1 EP 0795682 A1 EP0795682 A1 EP 0795682A1 EP 97300729 A EP97300729 A EP 97300729A EP 97300729 A EP97300729 A EP 97300729A EP 0795682 A1 EP0795682 A1 EP 0795682A1
Authority
EP
European Patent Office
Prior art keywords
casing
fan
gas turbine
blade
flexible material
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
EP97300729A
Other languages
German (de)
English (en)
Other versions
EP0795682B1 (fr
Inventor
Jeremy Paul Goodwin
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
Publication of EP0795682A1 publication Critical patent/EP0795682A1/fr
Application granted granted Critical
Publication of EP0795682B1 publication Critical patent/EP0795682B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/30—Retaining components in desired mutual position
    • F05B2260/301—Retaining bolts or nuts
    • F05B2260/3011—Retaining bolts or nuts of the frangible or shear type
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/224—Carbon, e.g. graphite
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced

Definitions

  • This invention relates to gas turbine fan duct casings and more particularly to an improved containment ring for use within or forming a part of the fan duct casing.
  • Ducted fan gas turbine engines for powering aircraft conventionally comprise a core engine which drives a propulsive fan.
  • the fan in turn, comprises a number of radially extending aerofoil blades mounted on a common hub and enclosed within a generally cylindrical casing.
  • containment rings for gas turbine engine casings is well known. Such rings have previously been manufactured from metal or alternatively glass fibre or carbon fibre etc. They have normally formed an integral part of the compressor casing.
  • EP 0626 502 A1 discloses continuous lengths of material wound around rails which are mounted on the outer surface of the fan casing. The space between the rails is filled with discrete pieces of flexible material. Therefore, a detached blade initially breaks through the thin alloy casing, becomes 'blunted' by the discrete pieces which attached thereto and is then retained by the material wound around the rails.
  • a gas turbine casing assembly comprising an annular cross-section casing configured to surround an annular array of rotary aerofoil blades, said casing defining a radially outer surface and positioned therewith a plurality of layers of flexible material wound as continuous lengths around said casing characterised in that at least one substantially rigid panel is interposed between said flexible material and said annular cross-section casing.
  • the rigid panel serves to distribute the load of the detached blade, along the length of the carbon panel. This helps prevent the detached blade form cutting through the wound Kevlar and enables a the number of layers of flexible material to be reduced. Additionally the provision of the rigid panel also provides additional support in the event that the casing should develop a circumferential crack. In such circumstances the rigid panel would act as a secondary load path for the aerodynamic and inertia forces within the engine mountings.
  • the rigid panel is moulded from carbon fibre or steel.
  • the rigid panel may preferably comprise a frangible material.
  • Fig 1 is a schematic sectioned side view of the upper half of a ducted gas turbine engine having a casing in accordance with the present invention.
  • Fig 2 is a sectioned side view of part of the fan casing of the ducted fan gas turbine engine shown in Fig 1.
  • a ducted gas turbine engine shown at 10 is of generally conventional configuration. It comprises a core engine 11 which drives a propulsive fan 12 enclosed within a fan casing assembly 13. The exhaust from the fan 12 is divided into two flows. The first and largest flow is directed to the exterior of the engine 10 over an annular array of outlet guides 14 located at the downstream end of the fan casing 13. The outlet guide vanes 14 are generally radially extending and interconnect the fan casing 13 with the core engine 11. The remainder of the air flow from the fan 12 is directed into the core engine 11 where it is compressed and mixed with fuel before being combusted to drive the core engine 11 by conventional turbines.
  • the fan 12 comprises an annular array of radially extending aerofoil cross section blades 15 mounted on a common hub 16.
  • the core engine 11 drives the fan 12 at high speed.
  • all or part of one or more of the fan blades 15 could become detached from the remainder of the fan 12.
  • Such mechanical failure could arise, for example, as the result of a foreign body, such as a bird, impacting the fan.
  • the high rotational speed of the fan 12 ensures that any such detached fan blade 15 is flung radially outwards with great force towards the fan casing assembly.
  • the detached fan blade 15 should be contained within the fan casing 13. Thus it should not pass through the fan casing assembly 13 and cause damage to the aircraft upon which the engine 10 is mounted.
  • the fan casing 13 comprises an annular cross-section casing 13 which is supported from the core engine 11 by means of outlet guide vanes 14.
  • Flange 18 is provided at the upstream end of the casing to facilitate attachment of the casing to the engine intake and outlet guide vanes and to provide stiffening of the casing.
  • the radially inner surface of the fan casing 17 supports an annular liner 22 which surrounds the radially outer extents of the fan blades 15.
  • the liner 22 protrudes a significant distance radially inwardly so that it terminates immediately adjacent the radially outer tips 23 of the fan blades 15.
  • the liner 22 also supports an annular flow defining structure 31.
  • the majority of the liner 22 is formed from a metallic honeycomb material 24, part of which is axially inclined to follow the profile of the fan blade tips 23.
  • the radially inner surface of the fan blade is, however, provided with a coating 25 of a suitable abradable material. As the fan blades rotate during normal engine operation their tips 23 cut a path through the abradable coating 25. This ensures that the radial clearance between the liner 22 and the fan blade tips 23 is as small as possible, thereby minimising efficiency damaging air leakage across the blade tips 23.
  • the liner 22 performs two further important functions. Firstly it assists in the stiffening of fan casing 17. Clearly any lack of stiffness in the fan casing 17 could result in flexing of the liner 22 and the fan blade tips 23. Secondly, in the event that the whole or part of one of the fan blades 15 should become detached, the honeycomb construction of the liner 22 defines a region which the fan blade 15 or fan blade 15 portion can move into. This tends to minimise the possibly damaging interaction between the detached fan blade and the remaining fan blades 15 thereby causing additional engine damage.
  • the fan casing 17 is of such a thickness that in the event of a detached blade 15 or fan blade 15 portion coming into contact with it, it is pierced. Thus although the fan casing 17 alone is not capable of containing a detached fan blade 15 or fan blade portion 15 it does absorb some of the kinetic energy of the blade 15.
  • Containment of a detached fan blade 15 or fan blade portion 15 is provided by containment material which is provided around the radially inner surface of the fan casing 17. More specifically the portion of the radially outer surface of the fan casing 17 which is radially outwardly of the fan blade tips 23 and slightly upstream thereof, is provided with two annular axially spaced apart frangible rail members 26. The rail members 26 are attached to the fan casing 17 thereby providing additional stiffness of the casing 17.
  • the axial space between the rails 26 is filled with discrete pieces of flexible material 27 woven from aromatic polyamide fibres known as KEVLAR (KEVLAR is a registered trademark of Dupont Ltd).
  • KEVLAR is a registered trademark of Dupont Ltd.
  • the pieces 27 are held loosely together by cotton stitching.
  • a number of continuous layers of KEVLAR are wound around the fan casing 17 between the most downstream of the rails 26 and a region upstream of the fan casing flange 19. These layers provide blade containment.
  • a number of carbon fibre panels 30 are interposed between the fibrous patches and the wound layers of KEVLAR.
  • the panels are positioned over the rails 26 around which the layers of KEVLAR are wound.
  • the blunted detached blade then encounters the rigid panel 30 and detaches the rigid panel 30 from its fixed points 33.
  • the detached panel 30, under the force of the blade moves into the area of wound KEVLAR.
  • the impact of the moving blade on the KEVLAR is spread over a larger area which helps to minimise the cutting forces of the blade. This also has the advantage that less KEVLAR is required.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP19970300729 1996-03-13 1997-02-05 Anneau de protection pour une turbosoufflante Expired - Lifetime EP0795682B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB9605284A GB9605284D0 (en) 1996-03-13 1996-03-13 Gas turbine engine casing construction
GB9605284 1996-03-13

Publications (2)

Publication Number Publication Date
EP0795682A1 true EP0795682A1 (fr) 1997-09-17
EP0795682B1 EP0795682B1 (fr) 2000-05-03

Family

ID=10790319

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19970300729 Expired - Lifetime EP0795682B1 (fr) 1996-03-13 1997-02-05 Anneau de protection pour une turbosoufflante

Country Status (3)

Country Link
EP (1) EP0795682B1 (fr)
DE (1) DE69701831T2 (fr)
GB (1) GB9605284D0 (fr)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0952310A3 (fr) * 1998-04-20 2000-07-19 United Technologies Corporation Turbosoufflante avec boítier de soufflante résistant à la pénétration
EP1087104A2 (fr) * 1999-09-25 2001-03-28 Rolls-Royce Plc Système de retenu pour des aubes de turbine à gaz
EP1245791A2 (fr) 2001-03-30 2002-10-02 ROLLS-ROYCE plc Dispositif de rétention des aubes pour turbine à gaz
EP1336739A2 (fr) * 2002-02-15 2003-08-20 General Electric Company Boítier de turbosoufflante de suppression du bruit et résistant à la pénétration
US7076942B2 (en) 2002-12-20 2006-07-18 Rolls-Royce Deutschland Ltd & Co Kg Protective ring for the fan protective casing of a gas turbine engine
EP1884639A2 (fr) * 2006-08-03 2008-02-06 Rolls-Royce Deutschland Ltd & Co KG Anneau de protection contre les impacts de glace pour le carter de soufflante d'un moteur d'aéronef
EP1857655A3 (fr) * 2006-05-16 2009-03-25 Rolls-Royce plc Panneau de revêtement
US8888439B2 (en) 2011-03-04 2014-11-18 Rolls-Royce Plc Turbomachine casing assembly
US9169045B2 (en) 2010-11-29 2015-10-27 Rolls-Royce Plc Gas turbine engine blade containment arrangement

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB868197A (en) * 1956-09-28 1961-05-17 Rolls Royce Improvements in or relating to protective arrangements for use with rotating parts
FR2216174A1 (fr) * 1973-02-02 1974-08-30 Norton Co
US4547122A (en) * 1983-10-14 1985-10-15 Aeronautical Research Associates Of Princeton, Inc. Method of containing fractured turbine blade fragments
EP0286815A1 (fr) * 1987-04-15 1988-10-19 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Anneaux de rétention pour carter de turbomachine
US5336044A (en) * 1993-08-06 1994-08-09 General Electric Company Blade containment system and method
EP0626502A1 (fr) * 1993-04-07 1994-11-30 ROLLS-ROYCE plc Montage d'enveloppe pour une turbine à gaz
US5447411A (en) * 1993-06-10 1995-09-05 Martin Marietta Corporation Light weight fan blade containment system

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB868197A (en) * 1956-09-28 1961-05-17 Rolls Royce Improvements in or relating to protective arrangements for use with rotating parts
FR2216174A1 (fr) * 1973-02-02 1974-08-30 Norton Co
US4547122A (en) * 1983-10-14 1985-10-15 Aeronautical Research Associates Of Princeton, Inc. Method of containing fractured turbine blade fragments
EP0286815A1 (fr) * 1987-04-15 1988-10-19 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Anneaux de rétention pour carter de turbomachine
EP0626502A1 (fr) * 1993-04-07 1994-11-30 ROLLS-ROYCE plc Montage d'enveloppe pour une turbine à gaz
US5447411A (en) * 1993-06-10 1995-09-05 Martin Marietta Corporation Light weight fan blade containment system
US5336044A (en) * 1993-08-06 1994-08-09 General Electric Company Blade containment system and method

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0952310A3 (fr) * 1998-04-20 2000-07-19 United Technologies Corporation Turbosoufflante avec boítier de soufflante résistant à la pénétration
EP1087104A2 (fr) * 1999-09-25 2001-03-28 Rolls-Royce Plc Système de retenu pour des aubes de turbine à gaz
EP1087104A3 (fr) * 1999-09-25 2003-11-12 Rolls-Royce Plc Système de retenu pour des aubes de turbine à gaz
EP1245791A2 (fr) 2001-03-30 2002-10-02 ROLLS-ROYCE plc Dispositif de rétention des aubes pour turbine à gaz
EP1245791A3 (fr) * 2001-03-30 2004-10-13 ROLLS-ROYCE plc Dispositif de rétention des aubes pour turbine à gaz
EP1336739A2 (fr) * 2002-02-15 2003-08-20 General Electric Company Boítier de turbosoufflante de suppression du bruit et résistant à la pénétration
EP1336739A3 (fr) * 2002-02-15 2005-03-16 General Electric Company Boítier de turbosoufflante de suppression du bruit et résistant à la pénétration
US7076942B2 (en) 2002-12-20 2006-07-18 Rolls-Royce Deutschland Ltd & Co Kg Protective ring for the fan protective casing of a gas turbine engine
US7914251B2 (en) 2006-05-16 2011-03-29 Rolls-Royce, Plc Liner panel
EP1857655A3 (fr) * 2006-05-16 2009-03-25 Rolls-Royce plc Panneau de revêtement
EP1884639A2 (fr) * 2006-08-03 2008-02-06 Rolls-Royce Deutschland Ltd & Co KG Anneau de protection contre les impacts de glace pour le carter de soufflante d'un moteur d'aéronef
EP1884639A3 (fr) * 2006-08-03 2012-11-07 Rolls-Royce Deutschland Ltd & Co KG Anneau de protection contre les impacts de glace pour le carter de soufflante d'un moteur d'aéronef
US9169045B2 (en) 2010-11-29 2015-10-27 Rolls-Royce Plc Gas turbine engine blade containment arrangement
US8888439B2 (en) 2011-03-04 2014-11-18 Rolls-Royce Plc Turbomachine casing assembly
US8926263B2 (en) 2011-03-04 2015-01-06 Rolls-Royce Plc Turbomachine casing assembly
EP2495400A3 (fr) * 2011-03-04 2015-03-11 Rolls-Royce plc Ensemble de carter de turbomachine
EP2495401A3 (fr) * 2011-03-04 2015-03-11 Rolls-Royce plc Ensemble de carter de turbomachine

Also Published As

Publication number Publication date
EP0795682B1 (fr) 2000-05-03
DE69701831T2 (de) 2000-08-17
DE69701831D1 (de) 2000-06-08
GB9605284D0 (en) 1996-05-15

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