EP2896794B1 - Blisk - Google Patents

Blisk Download PDF

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Publication number
EP2896794B1
EP2896794B1 EP15150251.5A EP15150251A EP2896794B1 EP 2896794 B1 EP2896794 B1 EP 2896794B1 EP 15150251 A EP15150251 A EP 15150251A EP 2896794 B1 EP2896794 B1 EP 2896794B1
Authority
EP
European Patent Office
Prior art keywords
blisk
lid
blades
filler
disk part
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.)
Not-in-force
Application number
EP15150251.5A
Other languages
English (en)
French (fr)
Other versions
EP2896794A1 (de
Inventor
Mark Houle
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 EP2896794A1 publication Critical patent/EP2896794A1/de
Application granted granted Critical
Publication of EP2896794B1 publication Critical patent/EP2896794B1/de
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
    • F04D29/326—Rotors specially for elastic fluids for axial flow pumps for axial flow fans comprising a rotating shroud
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3061—Fixing blades to rotors; Blade roots ; Blade spacers by welding, brazing
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/002—Axial flow fans
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations

Definitions

  • the present invention relates to a blisk for a gas turbine engine.
  • a blisk is a component having a rotor disk part and integral blades.
  • An outer surface or rim of the disk part generally forms the inner working gas annulus of the engine.
  • blisks are configured to avoid, where possible, forced responses from resonance and flutter.
  • blisks lack inherent damping when compared to conventional bladed disk assemblies, and forced responses to resonances and flutter cannot always be avoided.
  • fixing the inner working gas annulus at the outer surface of the disk part also fixes the basic size and shape of the disk part, and thus reduces options for reconfiguring the blisk to avoid forced responses and flutter.
  • EP0077039 relates to a mixed flow cooling fan for an automotive internal combustion engine.
  • EP2332765 and US2011/030336 relate to blisks for gas turbine engines.
  • GB2463036 relates to a blisk for a gas turbine engine, the blades of the blisk have platforms and insert elements are provided between the platforms.
  • An aim of the present invention is to provide an improved blisk which is, for example, less susceptible to forced responses and flutter.
  • the present invention provides a blisk a for a gas turbine engine according to claim 1.
  • the annulus fillers rather than an outer surface or rim of the disk part, can thus form the inner working gas annulus of the engine.
  • the radius of the disk part can be reduced and the length of the blades increased.
  • Reducing the radius of the disk part can also allow the total weight of the blisk to be decreased.
  • annulus fillers can themselves act as damper elements between the blades, reducing blade resonances by physical contact with the blades.
  • the present invention provides a gas turbine engine, such as aeroengine, having the blisk of the first aspect.
  • the blisk may be a fan blisk or a compressor section blisk.
  • each blade may continue radially inwardly of the respective lines of contact such that if the lids are moved radially inwardly, all the regions of suction and pressure side surfaces of the blades thereby revealed radially outwardly of the lids are aerofoil surface regions.
  • Damping strips which extend along the opposite edges of the lid to contact the suction and pressure sides of the adjacent blades can help to improve the damping properties of the fillers.
  • the strips may be formed of elastomer.
  • the strips can be adhesively bonded to the lid.
  • the annulus fillers may provide frictional damping. For example, rubbing along the contact lines between the lids and the blades can provide frictional damping.
  • each annulus filler can be formed of a laminate a portion of whose lamina are elastomeric (the other portion can be e.g. metallic).
  • each annulus filler may provide beneath the lid one or more retention formations which each retains a respective hook formed at the outer surface of the disk part and thereby holds the filler in position between its adjacent blades under centrifugal loading.
  • the support structure can provide forward and rearward retention formations which respectively retain forward and rearward hooks formed at the outer surface of the disk part.
  • the retention formations and hooks may be formed such that, on build, the annulus filler can be slid axially into position between its adjacent blades to mate the hooks with the retention formations.
  • Damping pads e.g. formed of elastomer
  • the pads can be adhesively bonded to the retention formations.
  • the retention formations can be variously shaped. For example, they can be complimentary hooks to the disk part hooks.
  • the complimentary hooks can be at the ends of respective legs (provided by the support structure) extending radially inwardly from the underside of the lid.
  • Another option is for the retention formations to be straps which locate under the disk part hooks. The straps can extend between side walls (provided by the support structure) extending radially inwardly from the opposite edges of the lid.
  • each annulus filler may provide a front and/or rear engagement formation at the front and/or rear end of the lid, the engagement formation engaging with a respective engine component (such as an adjacent fairing) to axially hold the filler in position between its adjacent blades.
  • a respective engine component such as an adjacent fairing
  • the annulus filler may be formed from aluminium alloy, titanium alloy, composite material (such as carbon fibre reinforced plastic) or a combination thereof.
  • such materials are relatively lightweight, helping to reduce the weight of the blisk.
  • a lightweight filler will tend to be less damaging to the engine.
  • the blades may be welded (e.g. linear friction welded) to the disk part.
  • welded e.g. linear friction welded
  • a ducted fan gas turbine engine incorporating the invention is generally indicated at 10 and has a principal and rotational axis X-X.
  • the engine comprises, in axial flow series, an air intake 11, a propulsive fan 12, an intermediate pressure compressor 13, a high-pressure compressor 14, combustion equipment 15, a high-pressure turbine 16, an intermediate pressure turbine 17, a low-pressure turbine 18 and a core engine exhaust nozzle 19.
  • a nacelle 21 generally surrounds the engine 10 and defines the intake 11, a bypass duct 22 and a bypass exhaust nozzle 23.
  • air entering the intake 11 is accelerated by the fan 12 to produce two air flows: a first air flow A into the intermediate pressure compressor 13 and a second air flow B which passes through the bypass duct 22 to provide propulsive thrust.
  • the intermediate pressure compressor 13 compresses the air flow A directed into it before delivering that air to the high pressure compressor 14 where further compression takes place.
  • the compressed air exhausted from the high-pressure compressor 14 is directed into the combustion equipment 15 where it is mixed with fuel and the mixture combusted.
  • the resultant hot combustion products then expand through, and thereby drive the high, intermediate and low-pressure turbines 16, 17, 18 before being exhausted through the nozzle 19 to provide additional propulsive thrust.
  • the high, intermediate and low-pressure turbines respectively drive the high and intermediate pressure compressors 14, 13 and the fan 12 by suitable interconnecting shafts.
  • a blisk may be used to form the propulsive fan 12 or may be part of a compressor section 13, 14 of such an engine.
  • Figure 2 shows a close-up view of a blisk propulsive fan 12.
  • the blisk has a rotor disk part 30 and a circumferential row of fan blades 32.
  • Annulus fillers 34 shown in more detail in Figures 3 to 5 , bridge the gaps between adjacent blades.
  • Each annulus filler 34 has an outer lid 36 which forms the inner surface of the working gas annulus of the engine, and an inner support structure which connects to the disk part 30 to support the lid on the blisk 12. Opposite edges of the lid respectively contact the suction side aerofoil surface of one blade and the pressure side aerofoil surface of an adjacent blade along contact lines 38.
  • the annulus fillers 34 provide a number of advantages. They provide damping to the blades 32 by physical contact. This reduces aerofoil vibration from forced response and flutter, and thus improves the service life.
  • the fillers also offer more flexibility in the blisk design, allowing the outer rim of the disk part 30 of the blisk to be reduced in diameter. The overall weight of the blisk 12 may thus be reduced for a given application, as the diameter of the disc part is reduced. Further, the natural frequency of the blades can be reduced due to the increase in blade length. This can be of particular benefit if there is a need to reduce the frequency of the fundamental flap mode/first engine order resonance. For example, there may be a need to keep the fundamental flap mode/first engine order resonance below a particular engine speed to reduce the forcing level.
  • the aerofoil surfaces of the blade 32 continue uninterruptedly below the level of the lids 36. This allows design changes to be made to the engine whereby new annulus fillers can be installed whose lids have differently shaped air-washed surfaces.
  • Each annulus filler 34 is assembled between and interfaces with adjacent blades 32 on the blisk 12, thus effectively forming an annular ring out of the lids 36.
  • the ring covers the regions where the join welds (which may be linear friction welds) between the blades 32 and the disk part 30 are typically made, thereby making weld surface finish in these regions a less critical aerodynamic issue.
  • FIG. 3 shows front and rear hooks 40 machined integrally to the outer surface of the disk part 30.
  • the hooks can alternatively be welded to the disk part. They can be located spatially on the disk part to suit the particular intended application, e.g. they can be located closer to the leading and trailing edges of the disk part than shown.
  • the support structure of each filler comprises retention formations in the form of corresponding hooks 42 at the ends of respective legs 44 extending from the underside of the filler's lid. On build, the filler is slid axially into position between its adjacent blades so that the hooks 40, 42 mate with each other and provide radial retention of the fillers under centrifugal loading.
  • the filler's support structure can provide other configurations for the retention formations, such as straps running between side walls extending from the opposite edges of the filler, the straps locating in use underneath the hooks 40.
  • Axial retention of the annulus fillers 34 can be achieved by fixing an engagement formation 46 at the front of each filler to the disk part 30 or to a suitable adjacent fairing such as the engine nose cone 50.
  • Other filler configurations may adopt a single hook 42 with positive front and rear engagement of the filler.
  • the annulus filler is constructed of light alloy or composite material, such as aluminium, titanium, carbon fibre composite or a mixture of these materials.
  • Damping strips 48 can extend along the opposite edges of each lid 36 for contact with the adjacent blades 32.
  • the strips can be formed, for example, of elastomer, which may be adhesively bonded to the lid.
  • the strips are pre-formed to conform to the shape of the contacting aerofoil surfaces. Instead of such strips, however, frictional damping at the interfaces between the lids and the blades can be used.
  • damping pads at the interfaces between the mating hooks 40, 42.
  • Such pads can also be formed of elastomer and may be adhesively bonded to the filler hooks 42.
  • the legs of the annulus damper can be constructed in such a manner as to be flexible, e.g. as a laminate formed layers of metal and elastomer, so as to provide additional damping.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (9)

  1. Blisk (12) für eine Gasturbine, wobei die Blisk ein Rotorscheibenteil (30), eine umlaufende Reihe von Schaufeln (32), die sich vom Scheibenteil erstrecken und mit diesem integriert sind, hat und die Blisk ferner eine Vielzahl von Zwischenschaufelplattformen (34) aufweist, die die Zwischenräume zwischen benachbarten Schaufeln überbrücken;
    wobei jede Zwischenschaufelplattform eine Außenkappe (36), die eine Luftstromfläche für durch den Motor in einer axialen Richtung gesaugte Luft definiert, und eine innere Unterstützungskonstruktion, die an den Scheibenteil anschließt, um die Kappe auf der Blisk zu unterstützen, hat, wobei gegenüberliegende Ränder der Kappe jeweilige Berührungslinien (38) mit einer saugseitigen Schaufelblattfläche einer Schaufel und einer druckseitigen Schaufelblattfläche einer benachbarten Schaufel erzeugen, dadurch gekennzeichnet, dass die Kappe von jeder Zwischenschaufelplattform Dämpfungsstreifen (48) hat, die sich entlang den gegenüberliegenden Rändern der Kappe erstrecken, um die Saugseiten und Druckseiten der benachbarten Schaufeln zu berühren.
  2. Blisk nach Anspruch 1, wobei die saugseitigen und druckseitigen Schaufelblattflächen von jeder Schaufel sich radial einwärts von den jeweiligen Berührungslinien so fortsetzen, dass, wenn die Kappen radial einwärts bewegt werden, alle dadurch radial auswärts der Kappen freigelegten saugseitigen und druckseitigen Flächenbereiche der Schaufeln Schaufelblattflächenbereiche sind.
  3. Blisk nach einem der vorhergehenden Ansprüche, wobei die Unterstützungskonstruktion von jeder Zwischenschaufelplattform unterhalb der Kappe eine oder mehrere Rückhalteanordnungen bereitstellt, die jeweils einen jeweiligen an der Außenfläche des Scheibenteils gebildeten Haken (40) festhalten und dadurch die Plattform in Position zwischen deren benachbarten Schaufeln unter zentrifugaler Belastung halten.
  4. Blisk nach Anspruch 3, wobei die Rückhalteanordnungen und Haken so gebildet sind, dass die Zwischenschaufelplattform, aufgebaut, in Position zwischen deren benachbarten Schaufeln axial geschoben werden kann, um die Haken mit den Rückhalteanordnungen zusammenzufügen.
  5. Blisk nach einem der Ansprüche 3 oder 4, wobei sich Dämpfungspuffer an den Schnittstellen zwischen den Rückhalteanordnungen und den Haken befinden.
  6. Blisk nach einem der vorhergehenden Ansprüche, wobei die Unterstützungskonstruktion von jeder Zwischenschaufelplattform ein vorderes und/oder hinteres Eingriffsgebilde (46) am vorderen und/oder hinteren Ende der Kappe bereitstellt, wobei das Eingriffsgebilde mit einem jeweiligen Motorbauteil (50) eingreift, um die Plattform axial in Position zwischen deren benachbarten Schaufeln zu halten.
  7. Blisk nach einem der vorhergehenden Ansprüche, wobei die Zwischenschaufelplattform aus einer Aluminiumlegierung, Titanlegierung, einem Verbundwerkstoff oder eine Kombination daraus gefertigt ist.
  8. Blisk nach einem der vorhergehenden Ansprüche, wobei die Schaufeln am Scheibenteil angeschweißt sind.
  9. Gasturbinenmotor mit einer Blisk nach einem der vorhergehenden Ansprüche.
EP15150251.5A 2014-01-16 2015-01-07 Blisk Not-in-force EP2896794B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB201400756A GB201400756D0 (en) 2014-01-16 2014-01-16 Blisk

Publications (2)

Publication Number Publication Date
EP2896794A1 EP2896794A1 (de) 2015-07-22
EP2896794B1 true EP2896794B1 (de) 2017-03-15

Family

ID=50239060

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15150251.5A Not-in-force EP2896794B1 (de) 2014-01-16 2015-01-07 Blisk

Country Status (3)

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US (1) US20150198174A1 (de)
EP (1) EP2896794B1 (de)
GB (1) GB201400756D0 (de)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3183429A1 (de) * 2014-08-22 2017-06-28 Siemens Energy, Inc. Modulare turbinenschaufel mit separatem plattformabstützungssystem
US10294965B2 (en) 2016-05-25 2019-05-21 Honeywell International Inc. Compression system for a turbine engine
US10746031B2 (en) * 2017-07-18 2020-08-18 Rolls-Royce Corporation Annulus filler
US10670037B2 (en) * 2017-11-21 2020-06-02 General Electric Company Turbofan engine's fan blade and setting method thereof
US11078839B2 (en) 2018-01-22 2021-08-03 Rolls-Royce Corporation Composite nosecone
US11421538B2 (en) 2020-05-12 2022-08-23 Rolls-Royce Corporation Composite aerofoils
US11506083B2 (en) 2020-06-03 2022-11-22 Rolls-Royce Corporalion Composite liners for turbofan engines

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5865999A (ja) * 1981-10-12 1983-04-19 Nissan Motor Co Ltd 斜流型フアン
GB2251897B (en) * 1991-01-15 1994-11-30 Rolls Royce Plc A rotor
US6354780B1 (en) * 2000-09-15 2002-03-12 General Electric Company Eccentric balanced blisk
US7278821B1 (en) * 2004-11-04 2007-10-09 General Electric Company Methods and apparatus for assembling gas turbine engines
GB0611031D0 (en) * 2006-06-06 2006-07-12 Rolls Royce Plc An aerofoil stage and a seal for use therein
GB2463036B (en) * 2008-08-29 2011-04-20 Rolls Royce Plc A blade arrangement
US8667774B2 (en) * 2009-08-05 2014-03-11 The Boeing Company Coannular ducted fan
GB0919657D0 (en) * 2009-11-11 2009-12-23 Rolls Royce Plc Annulus filler for a gas turbine engine
GB201020857D0 (en) * 2010-12-09 2011-01-26 Rolls Royce Plc Annulus filler

Also Published As

Publication number Publication date
EP2896794A1 (de) 2015-07-22
GB201400756D0 (en) 2014-03-05
US20150198174A1 (en) 2015-07-16

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