WO2012090736A1 - ファン動翼及びファン - Google Patents
ファン動翼及びファン Download PDFInfo
- Publication number
- WO2012090736A1 WO2012090736A1 PCT/JP2011/079215 JP2011079215W WO2012090736A1 WO 2012090736 A1 WO2012090736 A1 WO 2012090736A1 JP 2011079215 W JP2011079215 W JP 2011079215W WO 2012090736 A1 WO2012090736 A1 WO 2012090736A1
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- WIPO (PCT)
- Prior art keywords
- fan
- hub
- blade
- leading edge
- tip
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
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- 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
- F01D5/141—Shape, i.e. outer, aerodynamic form
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- 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
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
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- 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
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
- F04D29/324—Blades
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- 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
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
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- 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
- the present invention relates to a fan blade used for a fan that takes air into a core flow path and a bypass flow path in an engine case of an aircraft engine.
- a vertical hub part perpendicular to the fan axis (aircraft engine axis) is formed, and the base end (radial inner end) of this vertical hub part is It is located at the hub end of the blade front edge.
- a rearwardly inclined midspan is formed from the tip (radially outer end) of the vertical hub to the midspan side of the leading edge of the rotor blade.
- the tip of the rearwardly inclined midspan is rearward of the base end. It tilts backward so as to be located on the side (downstream side).
- a forward inclined tip portion is formed from the tip of the backward inclined midspan portion to the tip end of the leading edge of the moving blade, and this forward inclined tip portion is inclined forward so that the distal end is located in front of the base end. is doing.
- the hub side (hub side portion) of the blade leading edge is not formed on the hub side of the blade leading edge.
- the cord length on the hub side of the fan rotor blade can be sufficiently ensured as compared with the case where it is tilted backward.
- the tip of the tip tip is tilted forward, the air inflow speed on the tip side becomes slower compared to the case where the tip side (tip side portion) of the leading edge of the rotor blade is tilted backward, and the fan movement Shock wave loss on the tip side of the wing can be reduced.
- the center of gravity of the fan rotor blade is prevented from being biased forward with the formation of the forward tilt tip part, and the stress near the hub end of the rotor blade leading edge is reduced. Can be reduced.
- the structural strength of the fan blade can be sufficiently secured, and the aerodynamic performance of the fan blade such as the pressure ratio on the hub side and the fan efficiency on the tip side can be improved.
- annular core passage formed in an engine case of an aircraft engine, and an annular bypass passage formed concentrically outside the core passage in the engine case.
- a fan rotor blade used for a fan for taking in air is provided with the following.
- a moving blade leading edge is formed on the hub side, and a vertical hub portion that is substantially perpendicular to an axis of the fan (an axis of the aircraft engine), and a tip of the vertical hub portion Rear tilted midspan that is formed from the (radially outer end) to the midspan side and is tilted backward (sweep to the rear) so that the tip is located on the rear side (downstream side) of the base end (radial inner end)
- a forwardly inclined tip portion formed forwardly (sweep forward) so that the distal end is located on the front side (upstream side) of the base end, and the hub end.
- the “fan blade” means not only a fan blade in a narrow sense but also a compressor blade. Further, “perpendicular to the fan axis” means within a range of ⁇ 5 degrees with respect to a plane perpendicular to the fan axis. Further, the “upstream side” refers to the upstream side as viewed from the mainstream flow direction, and the “downstream side” refers to the downstream side as viewed from the mainstream flow direction.
- the fan for taking in air is characterized by comprising the following. That is, the fan is provided in the engine case so as to be rotatable around an axis, and a fan disk having a plurality of fitting grooves formed on the outer peripheral surface at equal intervals along the circumferential direction; The fan rotor blade is provided to be fitted in the groove.
- FIG. 1 is a side view of a fan rotor blade according to the first embodiment of the present invention.
- FIG. 2 is a half sectional view of the front portion of the aircraft engine according to the first embodiment of the present invention.
- FIG. 3A is a diagram showing the relationship between the axial length of the leading edge of the fan blade from the predetermined position and the span ratio of the leading edge of the fan blade, and
- FIG. 3B is a diagram of the fan blade. It is a figure which shows the relationship between the sweep angle of a front edge, and the span ratio of the front edge of a fan rotor blade.
- FIG. 4 is a side view of the fan rotor blade according to the second embodiment of the present invention.
- FIG. 5A is a view taken along the line VV in FIG. 4, and FIG.
- FIG. 5B is a view corresponding to FIG. 5A, and shows a state where the rearward tilting hub portion is not provided.
- FIG. 6 is a diagram illustrating the relationship between the fan efficiency of the fan blade and the span ratio of the leading edge of the fan blade.
- FIG. 7A is a diagram illustrating a stress distribution state of the back surface of the fan rotor blade according to the embodiment during operation of the fan
- FIG. 7B is a back surface of the fan rotor blade according to the comparative example during operation of the fan. It is a figure which shows the stress distribution state.
- the fan 1 according to the first embodiment of the present invention includes an annular core flow path (main flow path) 5 formed in an engine case 3 of an aircraft engine, and a core flow in the engine case 3. Air is taken into a bypass channel 7 formed concentrically outside the channel 5.
- the engine case 3 includes a cylindrical core cowl 9, a cylindrical fan case 13 provided on the outside of the cylindrical core cowl 9 so as to surround a plurality of (only one shown) struts 11, and the like. It is made up of.
- the core flow path 5 is defined inside the core cowl 9, and the bypass flow path 7 is defined by the outer wall of the core cowl 9 and the inner wall of the fan case 13.
- a fan disk 15 is rotatably provided at the front portion of the core cowl 9 via a bearing 17, and the fan disk 15 includes a plurality of stages of low-pressure turbines (not shown) disposed behind the fan 1.
- a low-pressure turbine rotor (not shown) is coaxially and integrally connected.
- a plurality of fitting grooves (fitting notches) 19 are formed on the outer peripheral surface of the fan disk 15 at equal intervals along the circumferential direction.
- a fan rotor blade 21 is fitted in each fitting groove 19 of the fan disk 15, and between the bottom surface (back surface) of each fitting groove 19 of the fan disk 15 and each fan rotor blade 21.
- a plurality of spacers 23 are provided at the front and rear.
- An annular front retainer 25 that holds a plurality of fan rotor blades 21 from the front is integrally provided on the front side of the fan disk 15, and a plurality of fan rotor blades 21 are provided on the rear side of the fan disk 15.
- An annular rear retainer 27 is integrally provided to hold the rear from the rear.
- the front retainer 25 is integrally connected to a nose cone 29 that guides air, and the rear retainer 27 is coaxial with the low-pressure compressor rotor 33 in the low-pressure compressor 31 disposed on the rear side of the fan 1.
- the plurality of fan rotor blades 21 can be rotated integrally with the fan disk 15 and air can be taken into the core flow path 5 and the bypass flow path 7. it can.
- the fan rotor blade 21 is used for the fan 1 as described above, and is made of a metal such as a titanium alloy. Further, the fan rotor blade 21 includes a blade body 35.
- the blade body 35 has a back surface (negative pressure surface) 37 on one side and an abdominal surface (positive pressure surface) 39 on the other side. is doing.
- the leading edge of the blade body 35 is the moving blade leading edge 41 of the fan blade 21, and the trailing edge of the blade body 35 is the moving blade trailing edge 43 of the fan blade 21.
- a blade root 45 is integrally formed on the base end side of the blade body 35, and the blade root 45 has a dovetail 47 that can be fitted into the fitting groove 19 of the fan disk 15.
- the boundary portion (platform portion) between the wing body 35 and the blade root 45 is located on an extension of the inner wall surface of the core flow path 5.
- a vertical hub portion 49 is formed on the hub side of the moving blade leading edge 41, and the vertical hub portion 49 has an axial center ( Aircraft engine axis) is substantially perpendicular to S, in other words, defined to be within a range of ⁇ 5 degrees with respect to a plane perpendicular to the axis of fan 1. Yes.
- a rearwardly inclined midspan portion 51 is formed from the tip (radially outer end) of the vertical hub portion 49 to the midspan side of the moving blade leading edge 41.
- the rearwardly inclined midspan portion 51 is smoothly connected to the vertical hub portion 49, and is inclined rearward so that the distal end is located on the rear side (downstream side) with respect to the base end (radial inner end). .
- the rearward tilted midspan portion 51 sweeps rearward and has a negative sweep angle.
- the magnitude of the forward tilt angle (negative sweep angle) ⁇ m of the rearward tilted midspan portion 51 gradually increases from the proximal end side toward the distal end side toward the negative value side and reaches a local maximum value. It is getting smaller gradually.
- the imaginary curve defining the hub side edge of the moving blade front edge 41 has a minimum sweep angle at the rearward tilted midspan 51 as shown in FIG.
- a forward inclined tip portion 53 is formed from the tip of the backward inclined midspan portion 51 to the tip end (tip side) of the moving blade leading edge 41.
- the forward inclined tip portion 53 is smoothly connected to the backward inclined mid-span portion 51, and is inclined forward so that the distal end is located on the front side (upstream side) of the base end.
- the sweep angle ⁇ h of the forward tilting tip portion 53 is a positive value.
- the forward tilt angle (positive sweep angle) of the forward tilt tip portion 53 gradually increases from the proximal end side to the distal end side.
- a rearwardly inclined hub portion 55 is formed from the hub end of the moving blade front edge 41 to the base end of the vertical hub portion 49.
- the rearward tilted hub portion 55 is smoothly connected to the vertical hub portion 49 and tilted rearward so that the distal end is located on the rear side of the base end.
- the rearward tilt angle (negative sweep angle) ⁇ h of the rearward tilted hub portion 55 has a maximum value on the negative value side on the base end side, has a minimum value, and gradually increases toward the vertical hub portion 49.
- the vertical hub portion 49 having a sweep angle ⁇ h of approximately 0 degrees is smoothly connected. Therefore, an imaginary curve defining the hub side edge of the moving blade leading edge 41 reaches the rearward tilted midspan portion 51 from the rearward tilted hub portion 55 through the vertical hub portion 49 as shown in FIG.
- the sweep angle ⁇ h has a maximum value in a region where As a result, a static pressure distribution that presses the air flow against the hub side is generated on the back surface of the fan rotor blade 21, and separation on the hub side (separation of the air flow) can be reduced.
- the vertical hub portion 49, the rearward tilted midspan portion 51, etc. are defined as follows in relation to the total span length LA of the moving blade leading edge 41, etc.
- the span length L1 from the hub end of the moving blade leading edge 41 to the tip of the vertical hub portion 49 is 20 to 50%, preferably 30 to 40% of the total span length LA of the moving blade leading edge 41. % Is set.
- the reason why the span length L1 is set to 20% or more of the total span length LA is that when the span length L1 is set to less than 20% of the total span length LA, it is difficult to sufficiently improve the pressure ratio on the hub side.
- the span length L1 is set to 50% or less of the total span length LA. If the span length L1 is set to exceed 50% of the total span length LA, the span length of the rearward inclined mid-span portion 51 is shortened. This is because it is feared that the center of gravity is biased forward and excessive stress is generated near the hub end of the blade leading edge 41.
- the maximum value of the backward inclination angle ⁇ m of the backward inclined midspan portion 51 is set to 5 to 45 degrees, preferably 10 to 20 degrees.
- the maximum value of the rearward tilt angle ⁇ m of the rearward tilted mid-span portion 51 is set to 5 degrees or more. This is because there is a concern that excessive stress is generated in the vicinity of the hub end of the moving blade leading edge 41 in the forward direction.
- the maximum value of the rearward tilt angle ⁇ m of the rearward tilted midspan portion 51 is set to 45 degrees or less. If the maximum value of the rearward tilt angle ⁇ m exceeds 45 degrees, the center of gravity of the fan rotor blade 21 is biased rearward and This is because it is feared that an excessive stress is generated near the hub end of the rear edge 43.
- the span length L2 from the hub end of the blade leading edge 41 to the proximal end (radial inner end) of the forward inclined tip portion 53 is 60 to the total span length LA of the moving blade leading edge 41. It is set to 90%, preferably 75 to 85%.
- the span length L2 is set to 60% or more of the total span length LA. If the span length L2 is set to less than 60% of the total span length LA, the center of gravity of the fan rotor blade 21 is moved forward with the formation of the forward inclined tip portion 53. This is because there is a concern that excessive stress is generated near the hub end of the moving blade leading edge 41.
- the span length L2 is set to 90% or less of the total span length LA. If the span length L2 is set to exceed 90% of the total span length LA, the air inflow speed on the tip side increases, and the tip side of the fan rotor blade 21 This is because it is difficult to sufficiently reduce the shock wave loss.
- the maximum value of the forward tilt angle (positive sweep angle) ⁇ t of the forward tilt tip portion 53 is set to 5 to 45 degrees, preferably 10 to 20 degrees.
- the maximum value of the forward tilt angle ⁇ t of the forward tilt tip portion 53 is set to 5 degrees or more.
- the maximum value of the forward tilt angle ⁇ t of the forward tilt tip portion is set to 45 degrees or less.
- the maximum tilt angle ⁇ t is set to exceed 45 degrees, the center of gravity of the fan rotor blade 21 is biased forward as the forward tilt tip portion 53 is formed. This is because it is feared that an excessive stress is generated near the hub end of the moving blade leading edge 41.
- the span length L3 from the hub end of the blade leading edge 41 to the tip of the rearward tilting hub portion 55 is 5 to 25% of the total span length of the blade leading edge 41, preferably 10 to It is set to 20%.
- the span length L3 is set to 5% or more of the total span length. If the span length L3 is set to less than 5% of the total span length, a static pressure distribution is generated on the rear surface of the fan blade 21 to press the air flow toward the hub side. It is because it becomes difficult.
- the span length L3 is set to 25% or less of the total span length. If the span length L3 is set to exceed 25% of the total span length, the span length of the vertical hub portion 49 is shortened and the pressure ratio on the hub side is sufficiently increased. This is because it becomes difficult.
- the maximum value of the rearward tilt angle ⁇ h of the rearward tilt hub portion 55 is set to 5 to 45 degrees, preferably 15 to 25 degrees.
- the maximum value of the rearward tilt angle ⁇ h of the rearward tilted hub portion 55 is set to 5 to 45 degrees because static pressure that presses the air flow toward the hub side when set to less than 5 degrees or greater than 45 degrees. This is because it is difficult to generate the distribution on the back surface of the fan blade 21.
- the inventor of the present application Similar to the previously described prior art turbine blade according to the prior art, while reducing the stress in the vicinity of the hub end of the blade leading edge 41, it is possible to sufficiently secure the cord length on the hub side of the fan blade 21 and the fan. The shock wave loss on the tip side of the moving blade 21 can be reduced.
- the cord length on the hub side of the fan rotor blade 21 is sufficiently secured while reducing the stress near the hub end of the rotor blade leading edge 41, and the fan rotor blade 21
- the shock wave loss on the chip side can be reduced.
- the aerodynamic performance of the fan rotor blade 21, particularly the fan efficiency on the chip side can be improved with sufficient structural strength of the fan rotor blade 21.
- the efficiency of the aircraft engine can be improved.
- the fan rotor blade 57 according to the second embodiment of the present invention is used for the fan 1 of an aircraft engine, similarly to the fan rotor blade 21 according to the first embodiment of the present invention.
- the specific configuration of the fan rotor blade 57 is as follows.
- the fan rotor blade 57 includes a blade body 59.
- the blade body 59 is made of a thermosetting resin such as an epoxy resin, a phenol resin, or a polyimide resin, or a thermoplastic resin such as polyether ether ketone or polyphenylene sulfide, and carbon. It is made of a composite material with reinforcing fibers such as fibers, aramid fibers, or glass fibers.
- the wing body 59 has a laminated structure (multilayer structure) in the thickness direction (the thickness direction of the wing body 59).
- the wing body 59 has a back surface (negative pressure surface) 61 on one side and an abdominal surface (positive pressure surface) 63 on the other side. It is the moving blade trailing edge 65 of the wing 57.
- a blade root 67 is integrally formed on the base end side of the blade body 59, and the blade root 67 is formed of a thermosetting resin or a composite material of a thermoplastic resin and a reinforced fiber, like the blade body 59. Therefore, it has a laminated structure in the thickness direction (the thickness direction of the blade root 67).
- the blade root 67 has a dovetail 69 that can be fitted in the fitting groove 19 of the fan disk 15.
- the boundary between the blade body 59 and the blade root 67 is located on the extension of the inner wall surface of the core flow path 5 (see FIG. 2).
- a sheath 71 for protecting the front edge side of the wing body 59 is provided via a sheet-like adhesive, and the sheath 71 is made of a metal such as a titanium alloy.
- the inside of the sheath 71 has a hollow structure, it may have a solid structure, or a cushion material (not shown) may be provided inside the sheath 71.
- the front edge of the sheath 71 is a moving blade front edge 73 of the fan rotor blade 57, and a vertical hub portion 75 is formed on the hub side of the moving blade front edge 73 (the front edge of the sheath 71).
- a rearwardly inclined midspan portion 77 is formed from the tip end (radially outer end) of the hub portion 75 to the midspan side of the moving blade leading edge 73.
- a forward inclined tip portion 79 is formed from the tip of the rearward inclined midspan portion 77 to the tip end (tip side) of the moving blade leading edge 73, and from the hub end of the moving blade leading edge 73 to the vertical hub portion 75.
- a rearwardly inclined hub portion 81 is formed toward the proximal end.
- the vertical hub portion 75, the rearward tilted mid-span portion 77, the forward tilt tip portion 79, and the rearward tilt hub portion 81 are each the blade front edge 41 of the fan blade 21 according to the first embodiment of the present invention.
- the vertical hub portion 49, the rearward tilted mid-span portion 51, the forward tilted tip portion 53, and the rearward tilted hub portion 55 have the same configuration.
- the vertical hub part 75 grade
- the vertical hub part 49 etc. in the moving blade front edge 41 of the fan bucket 21 which concerns on 1st Embodiment of this invention. Since it has the same structure, there exists an effect
- the rearwardly inclined hub portion 81 is formed from the hub end of the front edge of the sheath 71 to the base end of the vertical hub portion 75, as shown in FIGS.
- the vicinity of the hub end of the front edge of the wing body 59 can be moved away from the front edge of the sheath 71.
- the thickness near the hub end of the leading edge of the blade body 59 is increased, the structural strength of the blade body 59 made of the composite material is sufficiently secured, and the durability of the fan rotor blade 57 is improved. be able to.
- the span length L1 is 37% of the total span length LA, the maximum value of the rear tilt angle ⁇ m is 15 degrees, the span length L2 is 80% of the total span length LA, the maximum value of the forward tilt angle ⁇ t is 15 degrees, and the span length L3 Except that the fan blade 21 (fan blade according to the embodiment) in which the maximum value of the rear tilt angle ⁇ h is set to 23 degrees and the rear tilt hub portion are omitted.
- a fan rotor blade having the same configuration as the fan rotor blade according to the example (fan rotor blade according to the comparative example) is an analysis target.
- the span length L1 is 30 to 40% of the total span length LA
- the maximum value of the rear tilt angle ⁇ m is 10 to 20 degrees
- the span length L2 is 75 to 85% of the total span length LA
- the front The same applies to the fan rotor blade 21 in which the maximum value of the inclination angle ⁇ t is set to 10 to 20 degrees
- the span length L3 is set to 10 to 20% of the total span length
- the maximum value of the rear inclination angle ⁇ h is set to 15 to 25 degrees. The result of analysis was obtained.
- the vertical hub portion is perpendicular to the axial center of the fan, the forward tilt tip portion is tilted forward, and the rearward tilted midspan portion is tilted backward. Therefore, as in the case of the turbine blade according to the prior art previously filed by the inventor of the present application, while reducing the stress near the hub end of the blade leading edge, the hub blade side of the fan blade is reduced. It is possible to ensure a sufficient cord length and reduce shock wave loss on the tip side of the fan rotor blade. In addition, since the rearwardly inclined hub portion is inclined rearward, a static pressure distribution is generated on the back surface of the fan rotor blade so as to press the airflow toward the hub side, and the hub side separation (airflow separation) Can be reduced.
- a plurality of the fan rotor blades are integrated with the fan disk by rotating the fan disk by operating the aircraft engine. And the air can be taken into the core flow path and the bypass flow path.
- the cord length on the hub side of the fan moving blade is sufficiently secured, and the shock wave loss on the tip side of the fan moving blade is reduced.
- the separation on the hub side can be reduced, the structural strength of the fan rotor blade is sufficiently secured, and the aerodynamic performance of the fan rotor blade, in particular, the fan efficiency on the chip side is improved. High efficiency of the aircraft engine can be achieved.
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Abstract
Description
本発明の第1実施形態について図1から図3(a)(b)を参照して説明する。なお、図面中、「FF」は、前方向、「FR」は、後方向をそれぞれ指している。
本発明の第2実施形態について図4及び図5(a)(b)を参照して説明する。
本発明の実施例について図6及び図7(a)(b)を参照して説明する。
本国際特許出願は米国指定に関し、2010年12月28日に出願された日本国特許出願第2010-292658号について米国特許法第119条(a)に基づく優先権の利益を援用し、当該開示内容を引用する。
Claims (5)
- 航空機エンジンのエンジンケース内に形成された環状のコア流路、及び前記エンジンケース内における前記コア流路の外側に同心上に形成された環状のバイパス流路に空気を取入れるファンに用いられるファン動翼において、
動翼前縁は、
ハブ側に形成され、前記ファンの軸心に対して垂直な垂直ハブ部と、
前記垂直ハブ部の先端からミッドスパン側にかけて形成され、先端が基端よりも後側に位置するように後傾した後傾ミッドスパン部と、
前記後傾ミッドスパン部の先端からチップ側にかけて形成され、先端が基端よりも前側に位置するように前傾した前傾チップ部と、
ハブ端から前記垂直ハブ部の基端にかけて形成され、先端が基端よりも後側に位置するように後傾した後傾ハブ部と、
を具備することを特徴とするファン動翼。 - 前記動翼前縁のハブ端から前記垂直ハブ部の先端までのスパン長は、前記動翼前縁の全スパン長の20~50%であり、
前記動翼前縁のハブ端から前記後傾ハブ部の先端までのスパン長は、前記動翼前縁の全スパン長の5~25%であり、
前記後傾ハブ部の後傾角の大きさの最大値は、5~45度であることを特徴とする請求項1に記載のファン動翼。 - 前記動翼前縁のハブ端から前記前傾チップ部の基端までのスパン長は、前記動翼前縁の全スパン長の60~90%であり、
前記前傾チップ部の前傾角の最大値は、5~45度であることを特徴とする請求項1に記載のファン動翼。 - 熱硬化性樹脂又は熱可塑性樹脂と強化繊維との複合材料により構成された翼体と、
前記翼体の基端側に一体形成され、熱硬化性樹脂又は熱可塑性樹脂と強化繊維との複合材料により構成された翼根と、
前記翼体の前縁側に設けられ、金属により構成され、前記翼体の前縁側を保護するシースとを具備し、
前記シースの前縁が前記動翼前縁であることを特徴とする請求項1に記載のファン動翼。 - 航空機エンジンのエンジンケース内に形成された環状のコア流路、及び前記エンジンケース内における前記コア流路の外側に同心上に形成されたバイパス流路に空気を取入れるファンにおいて、
前記エンジンケース内に軸心周りに回転可能に設けられ、外周面に複数の嵌合溝が周方向に沿って等間隔に形成されたファンディスクと、
前記ファンディスクの各嵌合溝に嵌合して設けられ、請求項1に記載のファン動翼とを具備することを特徴とするファン。
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201180062674.9A CN103270313B (zh) | 2010-12-28 | 2011-12-16 | 风扇动叶片及风扇 |
CA2822786A CA2822786C (en) | 2010-12-28 | 2011-12-16 | Fan rotor blade and fan |
EP11854281.0A EP2660475B1 (en) | 2010-12-28 | 2011-12-16 | Fan rotor blade and fan |
RU2013134982/06A RU2541479C1 (ru) | 2010-12-28 | 2011-12-16 | Лопатка ротора вентилятора и вентилятор |
US13/997,834 US9359064B2 (en) | 2010-12-28 | 2011-12-16 | Fan rotor blade and fan |
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JP2010292658A JP5703750B2 (ja) | 2010-12-28 | 2010-12-28 | ファン動翼及びファン |
JP2010-292658 | 2010-12-28 |
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US (1) | US9359064B2 (ja) |
EP (1) | EP2660475B1 (ja) |
JP (1) | JP5703750B2 (ja) |
CN (1) | CN103270313B (ja) |
CA (1) | CA2822786C (ja) |
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JP2015509162A (ja) * | 2012-01-30 | 2015-03-26 | スネクマ | ターボジェットファンブレード |
US20150377030A1 (en) * | 2013-03-15 | 2015-12-31 | United Technologies Corporation | Locally Extended Leading Edge Sheath for Fan Airfoil |
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US10408224B2 (en) | 2014-01-23 | 2019-09-10 | United Technologies Corporation | Fan blades with abrasive tips |
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FR2981118B1 (fr) * | 2011-10-07 | 2016-01-29 | Snecma | Disque aubage monobloc pourvu d'aubes a profil de pied adapte |
FR2983234B1 (fr) * | 2011-11-29 | 2014-01-17 | Snecma | Aube pour disque aubage monobloc de turbomachine |
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JP2015509162A (ja) * | 2012-01-30 | 2015-03-26 | スネクマ | ターボジェットファンブレード |
WO2014009628A1 (fr) * | 2012-07-12 | 2014-01-16 | Snecma | Aube de turbomachine ayant un profil configuré de manière à obtenir des propriétés aérodynamiques et mécaniques améliorées |
FR2993323A1 (fr) * | 2012-07-12 | 2014-01-17 | Snecma | Aube de turbomachine ayant un profil configure de maniere a obtenir des proprietes aerodynamiques et mecaniques ameliorees |
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US10408224B2 (en) | 2014-01-23 | 2019-09-10 | United Technologies Corporation | Fan blades with abrasive tips |
Also Published As
Publication number | Publication date |
---|---|
RU2541479C1 (ru) | 2015-02-20 |
EP2660475A4 (en) | 2016-10-26 |
EP2660475A1 (en) | 2013-11-06 |
US9359064B2 (en) | 2016-06-07 |
CA2822786A1 (en) | 2012-07-05 |
JP5703750B2 (ja) | 2015-04-22 |
JP2012140874A (ja) | 2012-07-26 |
CN103270313A (zh) | 2013-08-28 |
US20130323065A1 (en) | 2013-12-05 |
CN103270313B (zh) | 2016-07-06 |
RU2013134982A (ru) | 2015-02-10 |
EP2660475B1 (en) | 2019-11-06 |
CA2822786C (en) | 2015-05-26 |
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