WO2020171282A1 - Dispositif de protection de pale - Google Patents

Dispositif de protection de pale Download PDF

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Publication number
WO2020171282A1
WO2020171282A1 PCT/KR2019/004314 KR2019004314W WO2020171282A1 WO 2020171282 A1 WO2020171282 A1 WO 2020171282A1 KR 2019004314 W KR2019004314 W KR 2019004314W WO 2020171282 A1 WO2020171282 A1 WO 2020171282A1
Authority
WO
WIPO (PCT)
Prior art keywords
blade
protrusions
present
protrusion
hollow
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/KR2019/004314
Other languages
English (en)
Korean (ko)
Inventor
김학인
안종기
손명숙
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.)
Hanwha Aerospace Co Ltd
Original Assignee
Hanwha Aerospace Co 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 Hanwha Aerospace Co Ltd filed Critical Hanwha Aerospace Co Ltd
Publication of WO2020171282A1 publication Critical patent/WO2020171282A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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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
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • 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
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B47/00—Suction cups for attaching purposes; Equivalent means using adhesives
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B47/00—Suction cups for attaching purposes; Equivalent means using adhesives
    • F16B47/003—Suction cups for attaching purposes; Equivalent means using adhesives using adhesives for attaching purposes
    • 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
    • F05D2240/10—Stators
    • F05D2240/14—Casings or housings protecting or supporting assemblies within
    • 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

Definitions

  • the present invention relates to a protective device for a blade. Specifically, the present invention relates to a protective device that protects the blades of an aircraft gas turbine engine from external shocks and the like.
  • the core engine is designed to be small and the fan diameter is large.
  • the increase in the size of the fan increases the overall weight of the fan module and acts as a factor that increases the overall weight of the engine.
  • the composite fan blade for a gas turbine refers to a rotating body that is located at the foremost part of the engine and serves to inhale and compress air of a large flow rate and introduce it into the core flow path and the bypass flow path of the engine.
  • fan blades made of composite materials are susceptible to delamination of the leading edge due to collisions caused by the inflow of foreign substances and vibrations generated during operation. Such interlayer breakage causes damage to the engine by breaking or detaching the blade. To prevent such damage, attach a metal strip to the vulnerable area.
  • This metal strip is mainly made of Titanium, Ni-alloy, and Stainless steel materials and adopts forging, pressing, and processing methods.
  • the metal strip Since the fan blade is twisted in three dimensions to improve performance, the metal strip is designed in a shape obtained by subtracting the adhesive part of 0.2 ⁇ 0.4 mm thick and the end part (NOSE) of 1 mm ⁇ 2 mm thick.
  • NOSE end part
  • tight dimensional tolerance management is required for bonding with composite fan blades.
  • a large amount of surface treatment costs are required for processing and bonding of forged materials.
  • An object of the present invention is to provide a protective equipment for a blade manufactured by applying the AM (Addictive Manufacturing) method.
  • the blade protection equipment is connected to a blade of a gas turbine engine to protect the blade, the blade body portion formed to surround the blade; A hollow portion formed by being hollow in a predetermined shape at one end of the body portion; And a protrusion formed in a predetermined direction on one surface of the body portion connected to the blade, and the protective equipment for the blade is manufactured by applying an additive manufacturing (AM) method.
  • AM additive manufacturing
  • the blade may be connected to the body portion through an adhesive material.
  • the hollow portion may be formed by hollowing a single hole of a predetermined shape.
  • the hollow portion may be formed by hollowing a semi-elliptical hole.
  • the hollow portion may be formed by hollowing a plurality of holes having a predetermined shape.
  • the hollow portion may be formed by hollowing a semi-elliptical hole and a rectangular hole.
  • the semi-elliptical hole and the rectangular hole may be formed to be spaced apart by a predetermined interval.
  • the predetermined distance may be 0.5 mm.
  • the protrusion may include a plurality of protrusions, and the plurality of protrusions may be formed to be spaced apart at predetermined intervals between protrusions adjacent to one surface of the body.
  • the plurality of protrusions may include a first protrusion formed in a first direction and a second protrusion formed in a second direction.
  • first direction and the second direction may be perpendicular to each other.
  • the present invention applies the AM (Addictive Manufacturing) method to manufacture the protective equipment for the blade. Accordingly, the present invention has an effect of reducing the cost used for designing and manufacturing a mold required for manufacturing the existing blade protection equipment.
  • the present invention forms one end of the blade protection device in a hollow shape. Therefore, the present invention has the effect of reducing the weight of the protective equipment for the blade.
  • the present invention applies a protrusion shape to one surface of the blade protection device. Therefore, the present invention has the effect of improving the adhesion between the blade protection equipment and the blade.
  • FIG. 1 is a plan view schematically showing a blade protection device according to an embodiment of the present invention.
  • FIG. 2 is a diagram schematically showing a position where an adhesive material is applied to the protective equipment for a blade according to an embodiment of the present invention.
  • 3 to 5 are views showing the shape of a hollow portion of the blade protection equipment according to an embodiment of the present invention.
  • 6 to 11 are views showing the shape of the protrusion of the blade protection equipment according to an embodiment of the present invention.
  • FIG. 1 is a plan view schematically showing a blade protection device according to an embodiment of the present invention.
  • the protection equipment 1 for a blade according to an embodiment of the present invention is manufactured by applying a three dimensional printing method or an AM (Addictive Manufacturing) method.
  • the three dimensional printing method is a technology for manufacturing a three-dimensional object in a three-dimensional form by hierarchically stacking specific substances in the form of powder, liquid, and solid.
  • it is a technology that digitizes an object to be spherical into a virtual object through 3D graphic design and then stacks very thin sections one layer at a time to manufacture the result, which is also called Addictive Manufacturing (AM), and mechanically processes a three-dimensional object.
  • AM Addictive Manufacturing
  • It is a concept opposite to the manufacturing method of cutting or subtractive manufacturing.
  • the 3D printing method was first developed in 1984 and was partially used for product modeling and prototyping until the 2000s, but the scope of use has gradually expanded due to recent technological advances, such as consumer goods, electronic parts, automobiles, medical equipment, and office equipment. , Aerospace, aviation, and other industries.
  • the blade protection equipment 1 has an effect of reducing the cost used for designing and manufacturing the mold required for manufacturing the existing blade protection equipment. It will be described in detail for the configuration of the blade protection equipment (1) according to an embodiment of the present invention.
  • a protective device for a blade 1 includes a body 2, a hollow 3, and a protrusion 4.
  • FIG. 1 is a plan view as viewed from the top of the blade protection equipment 1 according to an embodiment of the present invention.
  • the body portion 2 is formed to surround the blade. Specifically, the body portion 2 is formed in a semi-elliptical shape as shown in FIG. 1, and has one side open so that the blade can be inserted. At this time, the body portion 2 includes a nose portion 21 in which the hollow portion 3 is formed and a side portion 23 in which the protrusion portion 4 is formed.
  • the hollow part 3 is formed by being hollow in a predetermined shape at one end of the body part 2. Specifically, the hollow portion 3 is formed by being hollow in the predetermined shape in the nose portion 21 of the body portion (2). The specific shape of the hollow part 3 will be described later with reference to FIGS. 3 to 5.
  • the protrusion 4 is formed in a predetermined direction on one surface of the body 2 connected to the blade. Specifically, the protrusions 4 are formed on the side surfaces 23 of the body 2 in a predetermined direction. The specific shape of the protrusion 4 will be described later with reference to FIGS. 6 to 8.
  • FIG. 2 is a diagram schematically showing a position where an adhesive material is applied to the protective equipment for a blade according to an embodiment of the present invention.
  • the adhesive material 5 is applied to the side surface 23 of the body 2. That is, the protective equipment 1 for a blade according to an embodiment of the present invention is connected to the blade by applying an adhesive material 5 to the side surface 23 of the body 2.
  • FIGS. 3 to 5 are views showing the shape of a hollow portion of the blade protection equipment according to an embodiment of the present invention.
  • the shape of the hollow portion 3 shown in FIGS. 3 to 5 is for an example, and the shape of the hollow portion 3 may have a shape other than those shown in FIGS. 3 to 5. .
  • the hollow part 3 is formed by hollowing out a single hole of a predetermined shape. Specifically, in FIG. 3, it can be seen that the hollow part 3 is formed by hollowing the semi-elliptical hole 31. At this time, in the hollow part 3, the semi-elliptical hole 31 has a first gap d1 with both sides of the nose part 21, and the gap between both sides of the nose part 21 is a second gap ( It may be formed such that one end point of the half-oval-shaped hole 31 is disposed at the position d2).
  • the first distance d1 may be 0.5 mm
  • the second distance d2 may be 1.5 mm to 2.0 mm.
  • the hollow part 3 is formed by hollowing out a plurality of holes having a predetermined shape. Specifically, in FIG. 4, it can be seen that the hollow part 3 is formed by hollowing the rectangular hole 32 and the semi-elliptical hole 33. At this time, in the hollow part 3, one end point of the semi-elliptical hole 31 is disposed at a position where the gap between both sides of the nose part 21 is the second gap d2, and the rectangular hole 32
  • the holes 33 having a semi-elliptical shape may be formed to be spaced apart by a third interval d3.
  • the second interval d2 may be 1.5 mm to 2.0 mm
  • the third interval d3 may be 0.5 mm.
  • the hollow part 3 is formed by hollowing out a plurality of holes having a predetermined shape. Specifically, in FIG. 5, it can be seen that the hollow part 3 is formed by hollowing out the plurality of holes 34, 35, 36, and 37 in a truss structure. At this time, in the hollow part 3, one end point of the plurality of holes 34, 35, 36, 37 is disposed at a position where the gap between both sides of the nose part 21 is the second gap d2, and the plurality of holes 34 , 35, 36, 37) may be formed to be spaced apart by a fourth distance d4.
  • the second interval d2 may be 1.5 mm to 2.0 mm
  • the fourth interval d4 may be 0.5 mm.
  • the blade protection device 1 has a hollow part 3 formed by being hollow in a predetermined shape in the nose part 21, which is one end of the body part 2, to protect the blade. There is an effect of significantly reducing the weight of the equipment (1).
  • 6 to 11 are views showing the shape of the protrusion of the blade protection equipment according to an embodiment of the present invention.
  • the protrusion 3 includes a plurality of protrusions, and the plurality of protrusions are formed to be spaced apart at a predetermined interval between protrusions adjacent to the side part 23 which is one surface of the body part 2.
  • FIG. 6 is a plan view as viewed from the top of the blade protection equipment 1 according to an embodiment of the present invention
  • FIG. 7 is a body part 2 of the blade protection equipment 1 according to an embodiment of the present invention.
  • the protrusion 3 includes a plurality of protrusions 41 formed in the first direction, and the plurality of protrusions 41 are formed to be spaced apart at predetermined intervals between adjacent protrusions.
  • the plurality of protrusions 41 are described by marking only a single protrusion, but this is for convenience of explanation, and the plurality of protrusions 41 are all protrusions shown in Figs. 6 and 7 Means.
  • FIG. 8 is a plan view of the blade protection equipment 1 according to an embodiment of the present invention as viewed from above
  • FIG. 9 is a body part 2 of the blade protection equipment 1 according to an embodiment of the present invention. ) Is a view showing the side portion 23.
  • the protrusion 3 includes a plurality of protrusions 42 formed in the second direction, and the plurality of protrusions 42 are formed to be spaced apart at predetermined intervals between adjacent protrusions.
  • the plurality of protrusions 42 are described by marking only a single protrusion, but this is for convenience of explanation, and the plurality of protrusions 42 are all protrusions shown in FIGS. 8 and 9 Means.
  • the protrusion 3 includes a plurality of protrusions, and the plurality of protrusions are formed to be spaced apart at a predetermined interval between protrusions adjacent to the side surface 23, which is one surface of the body 2 I can.
  • FIG. 10 is a plan view as viewed from the top of the blade protection equipment 1 according to an embodiment of the present invention
  • FIG. 11 is a body part 2 of the blade protection equipment 1 according to an embodiment of the present invention. ) Is a view showing the side portion 23.
  • the protrusion 3 includes a first protrusion 43 formed in a first direction and a second protrusion 44 formed in a second direction, and the first protrusion 43 and the second It can be seen that the protrusions 44 are formed to be spaced apart at regular intervals between adjacent protrusions.
  • the plurality of protrusions 43 and 44 are described by denoting a number only for a single protrusion, but this is for convenience of explanation, and the plurality of protrusions 43 and 44 are shown in FIGS. 10 and 11 It means the entire projection shown.
  • first direction and the second direction may be perpendicular to each other.
  • first direction is a direction perpendicular to the body portion 2
  • second direction may be a direction parallel to the body portion 2.
  • the protective equipment for a blade 1 according to an embodiment of the present invention has a protrusion 4 formed in a predetermined direction on the side portion 21 that is one side of the body portion 2, so that the protective equipment for the blade (1) There is an effect of improving the adhesion between the and the blade.
  • the protective equipment 1 for a blade according to an embodiment of the present invention is manufactured in a form including the protrusion 4 by applying the AM (Addictive Manufacturing) method, so that a separate post for forming the protrusion 4 There is also the effect of eliminating the process.

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

Abstract

La présente invention concerne un dispositif de protection de pale. Un dispositif de protection de pale, selon un mode de réalisation de la présente invention, est un dispositif de protection de pale qui est relié à une pale d'un moteur de turbine à gaz et protège la pale, le dispositif de protection de pale comprenant : une partie de corps configurée pour entourer la pale ; une partie creuse qui est formée creuse dans une forme prédéterminée sur une extrémité de la partie de corps ; et des parties saillantes formées, dans une direction prédéterminée, sur une surface de la partie de corps qui est reliée à la pale. Le dispositif de protection de pale est fabriqué en utilisant une technique de fabrication additive (AM).
PCT/KR2019/004314 2019-02-21 2019-04-11 Dispositif de protection de pale Ceased WO2020171282A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
KR1020190020371A KR102777876B1 (ko) 2019-02-21 2019-02-21 블레이드용 보호 장비
KR10-2019-0020371 2019-02-21

Publications (1)

Publication Number Publication Date
WO2020171282A1 true WO2020171282A1 (fr) 2020-08-27

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PCT/KR2019/004314 Ceased WO2020171282A1 (fr) 2019-02-21 2019-04-11 Dispositif de protection de pale

Country Status (2)

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KR (1) KR102777876B1 (fr)
WO (1) WO2020171282A1 (fr)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20080075601A1 (en) * 2006-09-26 2008-03-27 Snecma Composite turbomachine blade with metal reinforcement
US20120152893A1 (en) * 2010-12-21 2012-06-21 United Technologies Corporation Method for securing a sheath to a blade
WO2014158245A1 (fr) * 2013-03-14 2014-10-02 Hodgson Benedict N Profil aérodynamique avec renfort de bord d'attaque
US20160208624A1 (en) * 2015-01-16 2016-07-21 Hamilton Sundstrand Corporation 3d printing of lead edge protective sheaths
US9664201B2 (en) * 2011-08-10 2017-05-30 Snecma Method of making protective reinforcement for the leading edge of a blade

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0815567D0 (en) * 2008-08-28 2008-10-01 Rolls Royce Plc An aerofoil

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20080075601A1 (en) * 2006-09-26 2008-03-27 Snecma Composite turbomachine blade with metal reinforcement
US20120152893A1 (en) * 2010-12-21 2012-06-21 United Technologies Corporation Method for securing a sheath to a blade
US9664201B2 (en) * 2011-08-10 2017-05-30 Snecma Method of making protective reinforcement for the leading edge of a blade
WO2014158245A1 (fr) * 2013-03-14 2014-10-02 Hodgson Benedict N Profil aérodynamique avec renfort de bord d'attaque
US20160208624A1 (en) * 2015-01-16 2016-07-21 Hamilton Sundstrand Corporation 3d printing of lead edge protective sheaths

Also Published As

Publication number Publication date
KR102777876B1 (ko) 2025-03-10
KR20200102143A (ko) 2020-08-31

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