WO2015015207A1 - Capuchon d'extrémité pour pale de ventilateur - Google Patents

Capuchon d'extrémité pour pale de ventilateur Download PDF

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Publication number
WO2015015207A1
WO2015015207A1 PCT/GB2014/052342 GB2014052342W WO2015015207A1 WO 2015015207 A1 WO2015015207 A1 WO 2015015207A1 GB 2014052342 W GB2014052342 W GB 2014052342W WO 2015015207 A1 WO2015015207 A1 WO 2015015207A1
Authority
WO
WIPO (PCT)
Prior art keywords
tip
tip cap
insert portion
fan blade
recess
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.)
Ceased
Application number
PCT/GB2014/052342
Other languages
English (en)
Inventor
Philip Stanley GRAINGER
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.)
Composite Technology and Applications Ltd
Original Assignee
Composite Technology and Applications 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 Composite Technology and Applications Ltd filed Critical Composite Technology and Applications Ltd
Publication of WO2015015207A1 publication Critical patent/WO2015015207A1/fr
Anticipated expiration legal-status Critical
Ceased 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04—Antivibration arrangements
    • F01D25/06—Antivibration arrangements for preventing blade vibration
    • 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/16—Form or construction for counteracting blade vibration
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • 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
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • This invention relates to a fan blade for a gas turbine engine.
  • the invention relates to a tip cap for such a fan blade, a fan blade having a tip cap, a method of manufacturing a tip cap and a method of designing a tip cap.
  • a turbofan engine has a fan comprising a plurality of fan blades towards its upstream end.
  • Modern fan blades typically have a complex highly swept and twisted shape optimised for aerodynamic performance.
  • the fan In use, the fan is driven to rotate by a turbine of the engine so that each fan blade accelerates air into the engine and provides propulsive thrust.
  • the performance of the gas turbine engine is improved by having a close fit between the fan blade tips and the inner gas-washed surface of the containment arrangement surrounding the fan.
  • Known containment arrangements comprise an inner abradable layer which defines the gas-washed surface, so as to achieve a close fit between the tips of the fan blades and the gas-washed surface.
  • a composite material generally comprises two or more constituent materials having different material properties, for example, strength and ductility.
  • a composite material may comprise a matrix material and a fibre reinforcement material.
  • the aerodynamic load on the fan blade typically acts on the blade in a direction which tends to increase the twist of the blade.
  • the centrifugal load on the blade due to the rotation of the blade introduces forces which tend to decrease the twist of the blade.
  • the centrifugal load distribution depends on the mass distribution of the fan blade.
  • the twist and/or untwist forces acting on a fan blade typically influence the radial position of the tip of the fan blade. In other words, the radial tip displacement from the design condition is influenced by the aerodynamic forces and centrifugal forces acting on the blade. It is known for fan blades to exhibit flutter under certain operating conditions of the turbofan engine in which they are installed.
  • known flutter modes include a leading edge and trailing edge tip flap mode, in which a portion of the blade towards the tip may oscillate or flap around a notional flap axis which is inclined to the spanwise and chordwise directions of the blade.
  • flutter is known to occur under certain operating conditions, it may be necessary for the control system of the engine to limit the operation of the engine to avoid those conditions.
  • Such limitations reduce the allowable operational envelope of the engine, and may require complicated control and safety procedures to ensure that the engine is operated within the allowable envelope.
  • a tip cap for a fan blade of a gas turbine engine comprising: a tip portion; and an insert portion arranged to be received in a recess of an aerofoil of a fan blade; wherein the insert portion comprises regions of different density.
  • the regions of different density may be provided by different materials
  • the regions of different density may comprise first and second materials respectively.
  • the second material may be denser than the first material.
  • the insert portion may predominantly comprise the first material.
  • a region comprising the second material may be disposed substantially at a central chord-wise portion of the insert.
  • a region comprising the second material may be disposed substantially at a leading edge chord-wise position and/or a region comprising the second material may be disposed substantially at a trailing-edge chord-wise position.
  • the insert portion may be a monolithic structure. That is to say, the insert portion may be a unitary body in which the regions of different density are not separable from each other without destroying the body.
  • the insert portion may comprise a support structure comprising the first material to which at least one body comprising the second material may be mounted.
  • the first aspect of the present invention also provides a fan blade for a gas turbine engine comprising a tip cap in accordance with the first aspect of the invention.
  • a fan blade for a gas turbine engine comprising: an aerofoil having a tip recess for receiving an insert portion of a tip cap; a tip cap having a tip portion and an insert portion, the insert portion having at least one cut-out; wherein the insert portion of the tip cap is disposed within the tip recess of the aerofoil, and wherein a void is defined by the cut-out within the recess.
  • the cut-out or at least one of the cut-outs may be formed in a central chord-wise portion of the insert portion. Alternatively, or in addition, the cut-out or at least one of the cut-outs may be formed in a leading-edge chord-wise portion of the insert portion and/or the cut-out or at least one of the cut-outs may be formed in a trailing-edge chord-wise portion of the insert portion. The cut-out or at least one of the cut-outs may extend span-wise or transverse to the chord of the blade. The void may be unfilled with any solid or liquid material.
  • the aerofoil may be hollow.
  • the fan blade may be made from a metallic material such as titanium or a titanium alloy.
  • At least the aerofoil of the fan blade may be made from a composite material.
  • the fan blade may comprise leading edge and/or trailing edge metalwork and/or tip metalwork.
  • the tip metalwork may define the recess for the insert portion of the tip cap.
  • the tip cap of a fan blade in accordance with the second aspect of the invention may be in accordance with the first aspect of the invention.
  • a tip cap comprising: a tip portion; and an insert portion arranged to be received in a recess of an aerofoil of a fan blade; wherein the insert portion comprises regions of different density; the method comprising a stereo lithographic process in which the regions of different density are produced from different materials.
  • the different materials may be different metal compositions.
  • the stereo lithographic process may, for example, be an Additive Layer Manufacturing (ALM) process.
  • ALM Additive Layer Manufacturing
  • At least one region of low density may be produced from aluminium or titanium, and at least one region of high density may be produced from depleted uranium, nickel or tungsten.
  • the respective materials may be deposited at different regions of the workpiece during the manufacturing process.
  • a method of designing a tip cap of a fan blade for a gas turbine engine comprising: an aerofoil having a tip recess for receiving an insert portion of a tip cap; a tip cap having a tip portion and an insert portion, wherein the insert portion of the tip cap is disposed within the tip recess of the aerofoil, the method comprising the steps of: defining at least a first tip cap and a second tip cap, the insert portions of the tip caps having different chord-wise mass distributions; determining at least one of the flutter characteristics and the tip displacement characteristics of fan blades comprising the respective tip caps; and selecting one of the tip caps based on the flutter characteristics and/or tip displacement characteristics.
  • At least one of the first and second tip caps may be in accordance with the first aspect of the invention.
  • a fan blade comprising at least one of the first and second tip caps may be in accordance with the second aspect of the invention.
  • the method may be a computer implemented method.
  • the second tip cap may be defined based on the flutter characteristics and/or the tip displacement characteristics of at least a first tip cap as part of an iterative process.
  • the invention may comprise any combination of the features and/or limitations referred to herein, except combinations of such features as are mutually exclusive.
  • Figure 1 schematically shows in cross-sectional view a turbofan engine having a fan disposed within a fan casing
  • Figure 2 schematically shows in exploded view a fan blade of the fan of Figure 1 , comprising an aerofoil provided with a tip cap;
  • Figure 3 schematically shows in perspective view a first embodiment of a tip cap
  • Figure 4 schematically shows in perspective view a second embodiment of a tip cap
  • Figure 5 schematically shows in perspective view a third embodiment of a tip cap
  • Figure 6 schematically shows in cross section view the insert portion of the tip cap of Figure 5;
  • Figure 7 schematically shows a side view of a fourth embodiment of a tip cap
  • Figure 8 schematically shows in cross-sectional view the tip cap of Figure 7.
  • Figure 9 schematically shows a side view of a fifth embodiment of a tip cap
  • Figure 10 schematically shows in cross-sectional view the tip cap of Figure 9
  • Figure 1 1 schematically shows a side view of a sixth embodiment of a tip cap
  • Figure 12 schematically shows a cross-sectional view of the tip cap of Figure 1 1 ; and Figure 13 is a flowchart representing a tip cap design process.
  • the engine 6 shown in Figure 1 has a fan 2 housed within a fan casing comprising a containment 4.
  • the fan 2 comprises a plurality of fan blades 8, which extend from a fan disc 1 1 to the radially inner gas-washed surface of the containment 4.
  • the gas- washed surface of the containment arrangement 4 is provided by a radially inner abradable layer 9 of the containment arrangement 4.
  • the fan blade 8 comprises an aerofoil 10 and a tip cap 22 which, in the assembled fan blade 8, is fixedly secured to the aerofoil 10.
  • the aerofoil 10 has a twisted, swept, wide-chord form.
  • the aerofoil 10 predominantly comprises a composite body 12 which is bounded by leading edge, trailing edge and tip metalwork 14, 16, 18.
  • the leading edge and trailing edge metalwork 14, 16 is in the form of titanium alloy sheaths protecting the leading edge and trailing edge of the aerofoil 10.
  • the leading edge and trailing edge metalwork 14, 16 is bonded to the composite body 12 within corresponding recesses (not shown) such that the gas-washed surface of the aerofoil 10 is continuous over the metalwork 14, 16 and the composite body 12.
  • the leading edge and trailing edge metalwork 14, 16 is integrally formed with the tip metalwork 18 which is thus made from the same titanium alloy.
  • the tip metalwork 18 is also bonded to the composite body 12 such that the gas-washed surface of the aerofoil 10 is continuous over the composite body 12 and the tip metalwork 18.
  • the tip metalwork 18 occupies the radially outer portion of the aerofoil 10 of the fan blade 8, and defines a tip recess 20 having a radially outer opening for receiving an insert portion 26 of the tip cap 22, as will be described in detail below.
  • the tip recess 20 is of substantially uniform depth within the tip metalwork 18 (i.e. in a radial direction), and has a substantially uniform chordwise cross-section throughout its depth.
  • the chordwise cross-section of the recess is defined by the internal surfaces of the tip metalwork 18, so that in this embodiment the tip metalwork 18 provides a wall of substantially uniform thickness around the recess. Accordingly, the chordwise cross- section of the tip recess 20 is similar to the outer profile of the aerofoil 10 towards its tip.
  • the tip cap 22 comprises a tip portion 24 and an insert portion 26.
  • the tip portion comprises a coating of a thermally insulating material, for example, cobalt boron nitrate, so as to prevent transfer of heat generated by the tip portion 24 rubbing against the abradable layer 9 of the containment arrangement 4 to the insert portion 26, the tip recess 20 and the composite body 12 of the aerofoil 10.
  • the coating is electrodeposited
  • the tip portion 24 is integrally formed with the insert portion 26, and the insert portion 26 is fixedly secured to the tip metalwork 18, for example, by bonding or by a mechanical connection.
  • a notional benchmark insert portion may be defined as an insert portion of uniform density which fills the tip recess 20 defined by the inner walls of the tip metalwork 18. Consequently, the mass distribution of the benchmark insert portion is solely a function of the general profile of the tip recess.
  • insert portions according to the invention are configured to have particular mass distributions along their length (i.e. chordwise of the fan blade 8) which differ from the mass distribution of such a notional benchmark insert portion. The mass distributions of such insert portions are configured to influence the flutter characteristics and/or the displacement of the fan blade 8 under centrifugal load.
  • a tip cap comprising an insert portion having increased mass towards the leading edge and/or trailing edge may give a fan blade more favourable flutter characteristics when compared with the same fan blade comprising the notional benchmark insert portion.
  • the onset frequency of fan blade flutter may be increased when compared with a fan blade having the notional benchmark insert portion.
  • the tip cap 22 comprises an insert portion 26 having a cut-out 28 located over a substantially central chord-wise length of the insert portion and extending transverse to the chord of the insert portion 26.
  • the cut-out 28 defines a void within the recess 20, which is left unfilled, and so the mass of the insert portion 26 is concentrated at the leading and trailing ends of the insert portion 26.
  • the tip cap 32 of Figure 4 differs from the tip cap 22 shown in Figure 3 in that the insert portion 34 has two cut-outs 36, 38 located respectively in leading and trailing edge chordwise lengths of the insert portion.
  • the cut-outs 36, 38 extend transverse to the chord of the insert portion 34.
  • the cut-outs 36, 38 define voids within the recess 20,which is left unfilled, and so the mass of the insert portion 34 is concentrated at the central region of the insert portion.
  • the cut-outs 28, 36, 38 may extend fully or partially across the thickness of the respective insert portions 26, 34.
  • the tip cap 44 of Figures 5 and 6 differs from the tip cap 22 of Figure 3 in that the insert portion 46 has a cut-out 48 located over a substantially central chordwise length of the insert portion 46 and extending in a substantially spanwise direction of the insert portion.
  • the cut-out 48 is formed in the radially inner base of the insert portion 46 and projects radially outwardly into the insert portion 46.
  • the insert portions 26, 34, 46 of the tip caps 22, 32, 44 respectively are monolithic components having a substantially uniform composition and density.
  • the effect of the unfilled voids defined within the tip recess 20 is that a fan blade 8 comprising either one of the tip caps 22, 32, 44 has a different mass distribution at its tip when compared with the mass distribution of the same fan blade 8 having a tip cap provided with the notional benchmark insert portion as described above.
  • providing at least one cut-out extending over a chord-wise length of the insert portion over of a tip cap can be used to achieve a particular desired mass distribution of the tip cap.
  • the tip cap 52 shown in Figures 7 and 8 comprises an insert portion 54 of
  • the insert portion 54 does not comprise any cut-outs. Instead, the insert portion 54 comprises a low density region 56 composed of a low density material and two high density regions 58, 60 composed of a high density material. In this embodiment, the low density region 56 forms the predominant part of the insert portion 54 in that the entire insert portion 54 is entirely composed of the low density material except for two substantially cuboid high density regions 58, 60 embedded within the low density material and extending over a substantially leading edge chordwise length and a substantially trailing edge chordwise length of the insert portion 54 respectively.
  • the tip cap 62 shown in Figures 9 and 10 differs from the tip cap 52 shown in Figures 7 and 8 in that the insert portion 64 comprises a single high density region 68 embedded within a low density region 66 forming the predominant part of the insert portion 64.
  • the high density region 68 is embedded within and extends over a substantially central chord-wise length of the insert portion 64.
  • the tip caps 52, 62 comprise regions of different density which comprise different materials respectively.
  • the low density regions may be composed of aluminium, titanium, an aluminium alloy or a titanium alloy.
  • the high density regions may be composed of depleted uranium, tungsten, nickel, or alloys thereof.
  • a fan blade 8 comprising either one of the tip caps 52, 62 has a different mass distribution at its tip when compared with the mass distribution of the same fan blade 8 having a tip cap with a notional benchmark insert portion as described above.
  • providing regions of high density and low density in the insert portion can be used to achieve a particular desired mass distribution of a tip cap.
  • the insert portion of a tip cap may comprise any combination of cut-outs, low density regions and high density regions as illustrated above. For example, as shown in
  • a tip cap 70 according to an embodiment of the invention comprises an insert portion 72 having a predominant low density region 74 and high density regions 76, 78 embedded within the low density region 74 and extending over a substantially leading edge chord-wise length and a substantially trailing edge chord- wise length of the insert portion 72 respectively.
  • the insert portion 72 also comprises a cut-out 80 extending transverse to the chord of the insert portion 72 over a substantially central chord-wise length of the insert portion 72.
  • One method of securing a tip cap to the tip metalwork 18 of the aerofoil section 10 is to apply an adhesive to the insert portion of the tip cap and/or to the tip recess 20, insert the insert portion of the tip cap into the tip recess 20 and cause or allow the adhesive to cure so as to form a bond.
  • the insert portion may be fixedly secured within the tip recess 20 defined within the tip metalwork 18 by a mechanical connection.
  • Insert portion and tip portion of a tip cap may be manufactured separately and subsequently secured together, or may be integrally formed.
  • Insert portions having a substantially uniform composition such as the insert portions 26, 34, 46 of the tip caps 22, 32, 44 shown in Figures 3 to 6, may be manufactured in a two-step process in which the insert portion is first formed without any cut-outs, for example by a casting process, and in which a cut-out is subsequently machined in the insert portion.
  • the insert portion may be formed with one or more cut-outs, for example by a casting process.
  • Tip caps may also be manufactured using an additive manufacturing or direct metal deposition process, which is sometimes referred to as 3D printing or stereolithography.
  • an additive manufacturing process for creating insert portions having regions of different density two different materials are used.
  • the materials which may be in powder or granular form at the start of the additive manufacturing process, are selectively deposited in appropriate locations over successive layers to build up the low density regions and high density regions respectively.
  • the material deposited in each layer is bonded to the material of the previous layer or layers, for example, by laser sintering or electron beam melting.
  • An insert portion manufactured in this way has a monolithic structure, despite comprising distinct regions of different material. In other words, the high density regions and low density regions are integrally formed.
  • the invention also relates to a method of designing a tip cap for a fan blade, and in particular to a method of designing the insert portion of the tip cap so as to achieve a mass distribution which provides favourable flutter characteristics and/or tip
  • the method may be an automated or semi-automated method implemented in a computer, in which a plurality of fan blade models having different tip caps are defined, simulation conditions are set, static and/or dynamic optimisation criteria are set, static and/or dynamic analysis of the blade model is performed, and a suitable tip cap is selected, either as a final design or as a basis for a new variant design in an iterative process.
  • the fan blade model simulates a fan blade 8 as defined herein, and correspondingly comprises an aerofoil including a standard tip recess.
  • the tip recess is referred to as standard since it does not change during the automated method.
  • the fan blade model also includes a tip cap model comprising a tip portion and an insert portion.
  • the insert portion is defined by a number of variables which include: the number, shape, size and location of any low density regions, high density regions and cut-outs; and the material and/or density of the low density regions and high density regions.
  • the insert portion may be modelled as a single low density region or as a single high density region.
  • Static and/or dynamic simulation conditions are set which define the operating conditions at which static and/or dynamic analysis of the fan blade model is to be performed.
  • the simulation conditions may include all or a part of the flight envelope of the aircraft.
  • the simulation conditions may include air temperature, pressure, fan revolutions per minute and airflow characteristics (e.g. turbulence).
  • the simulation conditions may relate to only a part of the flight envelope of an aircraft, for example, a part in which it is known for fan blade flutter to occur.
  • Static and/or dynamic optimisation criteria are set depending on the desired static or dynamic performance of the fan blade. For example, it may be desirable to ensure that the tip displacement of the fan blade under static centrifugal load is reduced to a minimum. Further, it may be desirable that the dynamic response of the fan blade is such that flutter does not occur over a part or all of the operational envelope of the turbofan engine.
  • Static optimisation criteria may therefore be defined as a desired or a minimum tip displacement.
  • Dynamic optimisation criteria may be defined as a specific flutter onset frequency, or a safety threshold for the flutter onset frequency defined relative to the frequency of aerodynamic loading which the fan blade is subjected to at the associated simulation conditions.
  • the optimisation criteria may comprise multiple optimisation criteria for a multiobjective optimisation process.
  • Complex optimisation criteria may be defined based on desirable flutter and/or tip displacement characteristics at a plurality of different simulation conditions, as is known in the art of multiobjective optimisation. For example, for a gas turbine engine for an aircraft, it may be necessary to optimise the tip cap such that the flutter onset frequency remains above the aerodynamic loading frequency of a fan over all or a part of the flight envelope of the aircraft.
  • one embodiment of the automated method is an iterative method. A user or an automated process first defines the standard design criteria 202, the optimisation criteria 214 (as described above), termination criteria 210, and the static and/or dynamic simulation conditions 204 (as described above).
  • the standard design criteria 202 are constraints to which the tip cap models 170 must adhere, such as the size of the tip recess in the aerofoil 1 10 of the fan blade model 108 and materials which may be used.
  • the termination criteria 210 may be set by a user or selected from a predetermined set of termination criteria. For example, for an iterative process, the termination criteria may be a number of iterations to perform, or a minimum threshold between the flutter and/or tip displacement characteristics for the two most favourable tip cap models 170. There may also be a minimum number of iterations that must be performed (e.g. 100 iterations). In the iterative process, an initial tip cap model 170 is defined by a tip cap definition process 200, taking into account the standard design criteria 202.
  • the aerofoil model 1 10 is then combined with the tip cap model 170 to define a fan blade model 108.
  • Static and/or dynamic modelling 206 of the fan blade model 108 is performed based on the static and/or dynamic simulation conditions 204, to calculate the flutter and/or tip displacement characteristics of the fan blade model 108 having the respective tip cap model 170.
  • the tip cap model 170 and/or its design variables e.g. cut-out location and size, location and size of high density and/or low density regions
  • the termination criteria 210 are evaluated in an evaluation step 21 1 .
  • a new tip cap model 170 is defined in a definition process 212, based on the optimisation criteria 214 set or selected by the user, the standard design criteria 202 and the previous tip cap models 170 and their associated flutter and/or tip displacement characteristics, retrieved from the database 208.
  • the new tip cap model 170 having a different mass distribution from previous tip cap models 170, is defined by adjusting the variables that define the insert portion, as described above.
  • a new fan blade model 108 is then created and the process is repeated until the termination criteria 210 are met.
  • the optimum tip cap model 170 is selected in a selection step 216.
  • the design of the optimum tip cap model 170 may then be implemented in a manufacturing process and installed in an aerofoil 10 to form an optimum fan blade 8.
  • the definition of the plurality of tip caps 170, the performance of the static and/or dynamic analysis of fan blade models 108 comprising the respective tip caps 170, and the selection of an optimum tip cap 170 may proceed based on any number of simulation and selection procedures as are known in the art.
  • the simulation and selection procedure may be a brute force process in which a plurality of tip cap models 170 are initially defined, a corresponding plurality of fan blade models 108 comprising the tip cap models 170 are subsequently analysed, and a suitable tip cap model 170 is selected based on the optimisation criteria.
  • the simulation and selection procedure may use a design of experiments method, a Monte Carlo method, or any simulation and selection methodology as is known in the art.
  • an insert portion comprises one or more regions of high density material which are wholly embedded within low density material
  • a region of high density material may constitute a section of the insert portion adjacent to, but not embedded within, a region of low density material.
  • an insert portion comprises regions of high and low density material which are integrally formed, for example by an additive manufacturing process
  • regions of one material may be mechanically connected to regions of another material.
  • discrete regions may be mechanically connected by rivets, bolts, or any other suitable fastener.
  • Discrete regions may be bonded together.
  • the tip metalwork is of substantially constant thickness
  • the tip metalwork may be provided with reinforcement projections, or castellations, projecting into the tip recess and the insert portion of the tip cap may be provided with corresponding channels, such that the insert portion of the tip cap keys with the tip recess.
  • the insert portion may be mechanically connected to the tip metalwork defining the tip recess with at least one fastener.
  • the insert portion predominantly comprises regions of low density material with further regions of high density material, it will be appreciated that in other embodiments the insert portion may predominantly comprise regions of high density material, with further regions of low density material.
  • references in above disclosure to regions of low and/or high density material, or to regions having different densities relate to regions of solid material, and are not intended to refer to cut-outs, voids, or gas-filled or liquid-filled regions.
  • the tip cap may comprise enclosed voids, for example, when the tip cap is manufactured by an additive manufacturing process.

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

Abstract

La présente invention concerne un capuchon d'extrémité (22), (32), (44), (52), (62), (70) pour une pale de ventilateur (8) d'une turbine à gaz comprenant : une partie extrémité (24); et une partie insert (26), (34), (46), (54), (64), (72) conçue pour être reçue dans un évidement (20) d'un profil aérodynamique (10) d'une pale de ventilateur (8), la partie insert comprenant des régions de différentes densités. Une autre pale de ventilateur (8) pour une turbine à gaz comprend : un profil aérodynamique (10) présentant un évidement d'extrémité (20) permettant de recevoir une partie insert d'un capuchon d'extrémité; un capuchon d'extrémité (22), (32), (44), (52), (62), (70) présentant une partie extrémité (24) et une partie insert (26), (34), (46), (54), (64), (72), la partie insert présentant au moins une découpe (28), (36), (38), (48), (80); la partie insert du capuchon d'extrémité étant disposée à l'intérieur de l'évidement d'extrémité du profil aérodynamique, et un vide étant défini par la découpe à l'intérieur de l'évidement.
PCT/GB2014/052342 2013-07-30 2014-07-30 Capuchon d'extrémité pour pale de ventilateur Ceased WO2015015207A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB1313596.7 2013-07-30
GBGB1313596.7A GB201313596D0 (en) 2013-07-30 2013-07-30 A tip cap for a fan blade

Publications (1)

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WO2015015207A1 true WO2015015207A1 (fr) 2015-02-05

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PCT/GB2014/052342 Ceased WO2015015207A1 (fr) 2013-07-30 2014-07-30 Capuchon d'extrémité pour pale de ventilateur

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WO (1) WO2015015207A1 (fr)

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EP2963244A1 (fr) * 2014-07-02 2016-01-06 Rolls-Royce plc Insert de bout, aube rotative et moteur à turbine à gaz associés
EP3333369A1 (fr) * 2016-12-08 2018-06-13 United Technologies Corporation Pale de ventilateur présentant un ensemble pointe
KR20190036858A (ko) * 2017-09-28 2019-04-05 두산중공업 주식회사 압축기 블레이드, 압축기 블레이드용 압축기 블레이드 댐퍼, 압축기 블레이드를 포함하는 압축기 및 이를 포함하는 가스 터빈
US10533575B2 (en) 2017-09-06 2020-01-14 United Technologies Corporation Fan blade tip with frangible strip

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EP1772593A2 (fr) * 2005-10-04 2007-04-11 The General Electric Company Extrémité bicouche d'une aube
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EP2028342A2 (fr) * 2007-08-21 2009-02-25 United Technologies Corporation Procédé de réparation d'une extrémité d'aube de turbine
EP2096652A1 (fr) * 2008-02-27 2009-09-02 Ansaldo Energia S.P.A. Procédé et dispositif pour détecter les fréquences naturelles de vibration d'une pale de turbine
DE102009032549A1 (de) * 2009-07-10 2011-01-13 Mtu Aero Engines Gmbh Verfahren zum Mindern von Schwingungsamplituden
US7967565B1 (en) * 2009-03-20 2011-06-28 Florida Turbine Technologies, Inc. Low cooling flow turbine blade
CA2696274A1 (fr) * 2010-03-11 2011-09-11 General Electric Company Procede de fabrication de profils de turbines et de structures d'inclinaison connexes

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FR2502242A1 (fr) * 1981-03-20 1982-09-24 Gen Electric Embout rapporte pour aube de rotor
EP1772593A2 (fr) * 2005-10-04 2007-04-11 The General Electric Company Extrémité bicouche d'une aube
US20070258825A1 (en) * 2006-05-08 2007-11-08 General Electric Company Turbine blade tip cap
EP2028342A2 (fr) * 2007-08-21 2009-02-25 United Technologies Corporation Procédé de réparation d'une extrémité d'aube de turbine
EP2096652A1 (fr) * 2008-02-27 2009-09-02 Ansaldo Energia S.P.A. Procédé et dispositif pour détecter les fréquences naturelles de vibration d'une pale de turbine
US7967565B1 (en) * 2009-03-20 2011-06-28 Florida Turbine Technologies, Inc. Low cooling flow turbine blade
DE102009032549A1 (de) * 2009-07-10 2011-01-13 Mtu Aero Engines Gmbh Verfahren zum Mindern von Schwingungsamplituden
CA2696274A1 (fr) * 2010-03-11 2011-09-11 General Electric Company Procede de fabrication de profils de turbines et de structures d'inclinaison connexes

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2963244A1 (fr) * 2014-07-02 2016-01-06 Rolls-Royce plc Insert de bout, aube rotative et moteur à turbine à gaz associés
US9670786B2 (en) 2014-07-02 2017-06-06 Rolls-Royce Plc Rotary blade with tip insert
EP3333369A1 (fr) * 2016-12-08 2018-06-13 United Technologies Corporation Pale de ventilateur présentant un ensemble pointe
US10495103B2 (en) 2016-12-08 2019-12-03 United Technologies Corporation Fan blade having a tip assembly
US10533575B2 (en) 2017-09-06 2020-01-14 United Technologies Corporation Fan blade tip with frangible strip
KR20190036858A (ko) * 2017-09-28 2019-04-05 두산중공업 주식회사 압축기 블레이드, 압축기 블레이드용 압축기 블레이드 댐퍼, 압축기 블레이드를 포함하는 압축기 및 이를 포함하는 가스 터빈
KR102000350B1 (ko) * 2017-09-28 2019-07-15 두산중공업 주식회사 압축기 블레이드, 압축기 블레이드용 압축기 블레이드 댐퍼, 압축기 블레이드를 포함하는 압축기 및 이를 포함하는 가스 터빈

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