EP0795682B1 - Berstschutzeinrichtung für ein Bläsertriebwerk - Google Patents

Berstschutzeinrichtung für ein Bläsertriebwerk Download PDF

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Publication number
EP0795682B1
EP0795682B1 EP19970300729 EP97300729A EP0795682B1 EP 0795682 B1 EP0795682 B1 EP 0795682B1 EP 19970300729 EP19970300729 EP 19970300729 EP 97300729 A EP97300729 A EP 97300729A EP 0795682 B1 EP0795682 B1 EP 0795682B1
Authority
EP
European Patent Office
Prior art keywords
casing
fan
panel
blade
gas turbine
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 - Lifetime
Application number
EP19970300729
Other languages
English (en)
French (fr)
Other versions
EP0795682A1 (de
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/de
Application granted granted Critical
Publication of EP0795682B1 publication Critical patent/EP0795682B1/de
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.
  • 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 engine 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, at least one substantially rigid panel is interposed between said flexible material and said annular cross-section casing; characterised in that said rigid panel is frangible and is detachably mounted to said casing at spaced apart points on said panel.
  • 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 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.
  • a ducted gas turbine engine shown at is of generally conventional configuration. It comprises a core engine which drives a propulsive fan enclosed within a fan casing assembly. The exhaust from the fan is divided into two flows. The first and largest flow is directed to the exterior of the engine over an annular array of outlet guides located at the downstream end of the fan casing 13.
  • the outlet guide vanes are generally radially extending and interconnect the fan casing with the core engine. The remainder of the air flow from the fan is directed into the core engine where it is compressed and mixed with fuel before being combusted to drive the core engine by conventional turbines.
  • the fan comprises an annular array of radially extending aerofoil cross section blades 15 mounted on a common hub.
  • the core engine drives the fan at high speed.
  • all or part of one or more of the fan blades 15 could become detached from the remainder of the fan.
  • 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 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 is mounted.
  • 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 32.
  • 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 casing is, however, provided with a coating of a suitable abradable material. As the fan blades rotate during normal engine operation their tips 23 cut a path through the abradable coating. 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.
  • 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 28,29,31 of KEVLAR are wound around the fan casing 17 and the rails 26 on a region of the fan casing downstream of flange 18. These layers 28,29,31 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 29,31 of KEVLAR are wound.
  • the blunted detached blade 15 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 15, 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)

Claims (5)

  1. Gasturbinentriebwerks-Gehäuseaufbau (13), bestehend aus einem im Querschnitt ringförmigen Gehäuse (17), welches eine ringförmige Anordnung von rotierenden, stomlinienförmigen Schaufeln (15) umgibt, wobei das Gehäuse (17) eine radial äußere Oberfläche definiert und mit diesem mehrere Schichten aus flexiblem Material (29, 31) vorgesehen sind, die als kontinuierliche Längen um das Gehäuse (17) herumgewickelt sind, und wobei wenigstens eine im wesentlichen starre Platte (30) zwischen das flexible Material (29, 31) und das im Querschnitt ringförmige Gehäuse (17) eingefügt ist,
    dadurch gekennzeichnet, daß die starre Platte (30) brechbar und lösbar am Gehäuse (17) an Punkten (33) festgelegt ist, die auf der Platte (30) im Abstand zueinander liegen.
  2. Gasturbinentriebwerks-Gehäuseaufbau (13) nach Anspruch 1,
    dadurch gekennzeichnet, daß die starre Platte (30) eine Kohlenstoffaser-Platte ist.
  3. Gasturbinentriebwerks-Gehäuseaufbau (13) nach Anspruch 1 oder 2,
    dadurch gekennzeichnet, daß die starre Platte (30) am Gehäuse (17) an jedem Ende der Platte (30) festgelegt ist.
  4. Gasturbinentriebwerks-Gehäuseaufbau (13) nach einem der vorhergehenden Ansprüche,
    dadurch gekennzeichnet, daß die Schichten (29, 31) aus flexiblem Material aus gewebten aromatischen Polyamidfasern bestehen.
  5. Fanschaufel-Fangaufbau für ein Gasturbinentriebwerk, welches ein Fangehäuse (17) mit ringförmigem Querschnitt aufweist, das einen ringförmigen Aufbau von rotierenden, stromlinienförmigen Schaufeln (15) umgibt, wobei das Gehäuse (17) eine radial äußere Oberfläche definiert und mit einer Mehrzahl von Schichten aus flexiblem Material versehen ist, die als kontinuierliche Längen um das Gehäuse (17) gewickelt sind, wobei wenigstens eine im wesentlichen starre Platte (30) zwischen das flexible Material (29, 31) und das Gehäuse ringförmigen Querschnitts eingefügt ist,
    dadurch gekennzeichnet, daß die starre Platte (30) brechbar und lösbar am Gehäuse (17) an Punkten (33) befestigt ist, die auf der Platte (30) im Abstand zueinander liegen.
EP19970300729 1996-03-13 1997-02-05 Berstschutzeinrichtung für ein Bläsertriebwerk Expired - Lifetime EP0795682B1 (de)

Applications Claiming Priority (2)

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

Publications (2)

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

Family

ID=10790319

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19970300729 Expired - Lifetime EP0795682B1 (de) 1996-03-13 1997-02-05 Berstschutzeinrichtung für ein Bläsertriebwerk

Country Status (3)

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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102006036648A1 (de) * 2006-08-03 2008-02-07 Rolls-Royce Deutschland Ltd & Co Kg Eisschlagschutzring für das Fangehäuse einer Fluggasturbine

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6059524A (en) * 1998-04-20 2000-05-09 United Technologies Corporation Penetration resistant fan casing for a turbine engine
GB9922619D0 (en) * 1999-09-25 1999-11-24 Rolls Royce Plc A gas turbine engine blade containment assembly
GB0107970D0 (en) 2001-03-30 2001-05-23 Rolls Royce Plc A gas turbine engine blade containment assembly
US6619913B2 (en) * 2002-02-15 2003-09-16 General Electric Company Fan casing acoustic treatment
DE10259943A1 (de) 2002-12-20 2004-07-01 Rolls-Royce Deutschland Ltd & Co Kg Schutzring für das Fan-Schutzgehäuse eines Gasturbinentriebswerks
GB0609632D0 (en) 2006-05-16 2006-06-28 Rolls Royce Plc An ice impact panel
GB201020143D0 (en) 2010-11-29 2011-01-12 Rolls Royce Plc A gas turbine engine blade containment arrangement
GB201103682D0 (en) 2011-03-04 2011-04-20 Rolls Royce Plc A turbomachine casing assembly

Family Cites Families (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
FR2216174B1 (de) * 1973-02-02 1978-09-29 Norton Co
US4547122A (en) * 1983-10-14 1985-10-15 Aeronautical Research Associates Of Princeton, Inc. Method of containing fractured turbine blade fragments
EP0286815B1 (de) * 1987-04-15 1991-05-29 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Berstschutzring für Turbotriebwerksgehäuse
GB9307288D0 (en) * 1993-04-07 1993-06-02 Rolls Royce Plc Gas turbine engine casing construction
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 (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102006036648A1 (de) * 2006-08-03 2008-02-07 Rolls-Royce Deutschland Ltd & Co Kg Eisschlagschutzring für das Fangehäuse einer Fluggasturbine
US7780401B2 (en) 2006-08-03 2010-08-24 Rolls-Royce Deutschland Ltd & Co Kg Ice strike sheathing ring for the fan casing of an aircraft gas turbine

Also Published As

Publication number Publication date
GB9605284D0 (en) 1996-05-15
EP0795682A1 (de) 1997-09-17
DE69701831T2 (de) 2000-08-17
DE69701831D1 (de) 2000-06-08

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