US20170058916A1 - Gas turbine fan fairing platform and method of fairing a root leading edge of a fan blade of a gas turbine engine - Google Patents

Gas turbine fan fairing platform and method of fairing a root leading edge of a fan blade of a gas turbine engine Download PDF

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Publication number
US20170058916A1
US20170058916A1 US14/841,852 US201514841852A US2017058916A1 US 20170058916 A1 US20170058916 A1 US 20170058916A1 US 201514841852 A US201514841852 A US 201514841852A US 2017058916 A1 US2017058916 A1 US 2017058916A1
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United States
Prior art keywords
gas turbine
blade
platform
fairing
leading edge
Prior art date
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Abandoned
Application number
US14/841,852
Inventor
Sean A. Whitehurst
Michael A. Weisse
Jordan J. Franklin
Patrick James McComb
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.)
Pratt and Whitney Co Inc
RTX Corp
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United Technologies Corp
Pratt and Whitney Co Inc
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Filing date
Publication date
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Priority to US14/841,852 priority Critical patent/US20170058916A1/en
Assigned to PRATT & WHITNEY reassignment PRATT & WHITNEY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: WHITEHURST, SEAN A., MCCOMB, PATRICK JAMES, WEISSE, MICHAEL A., FRANKLIN, Jordan J.
Assigned to UNITED TECHNOLOGIES CORPORATION reassignment UNITED TECHNOLOGIES CORPORATION NUNC PRO TUNC ASSIGNMENT (SEE DOCUMENT FOR DETAILS). Assignors: FRANKLIN, Jordan J., MCCOMB, PATRICK JAMES, WEISSE, MICHAEL A., WHITEHURST, SEAN A.
Priority to EP16186865.8A priority patent/EP3139005B1/en
Assigned to UNITED TECHNOLOGIES CORPORATION reassignment UNITED TECHNOLOGIES CORPORATION CORRECTIVE ASSIGNMENT TO CORRECT THE MICHAEL A. WEISSE SIGNATURE DATE JUNE 6, 2016 & CORRECT ZIP CODE ON ASSIGNEE PREVIOUSLY RECORDED ON REEL 039136 FRAME 0495. ASSIGNOR(S) HEREBY CONFIRMS THE ASSIGNMENT. Assignors: FRANKLIN, Jordan J., WEISSE, MICHAEL A., MCCOMB, PATRICK JAMES, WHITEHURST, SEAN A.
Publication of US20170058916A1 publication Critical patent/US20170058916A1/en
Assigned to RAYTHEON TECHNOLOGIES CORPORATION reassignment RAYTHEON TECHNOLOGIES CORPORATION CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: UNITED TECHNOLOGIES CORPORATION
Assigned to RAYTHEON TECHNOLOGIES CORPORATION reassignment RAYTHEON TECHNOLOGIES CORPORATION CORRECTIVE ASSIGNMENT TO CORRECT THE AND REMOVE PATENT APPLICATION NUMBER 11886281 AND ADD PATENT APPLICATION NUMBER 14846874. TO CORRECT THE RECEIVING PARTY ADDRESS PREVIOUSLY RECORDED AT REEL: 054062 FRAME: 0001. ASSIGNOR(S) HEREBY CONFIRMS THE CHANGE OF ADDRESS. Assignors: UNITED TECHNOLOGIES CORPORATION
Abandoned 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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
    • 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
    • F04D29/38—Blades
    • F04D29/384—Blades characterised by form
    • 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
    • F04D29/70—Suction grids; Strainers; Dust separation; Cleaning
    • F04D29/701—Suction grids; Strainers; Dust separation; Cleaning especially adapted for elastic fluid pumps
    • F04D29/703—Suction grids; Strainers; Dust separation; Cleaning especially adapted for elastic fluid pumps specially for fans, e.g. fan guards
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • 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

  • Gas turbine engines typically include platforms near a root of a fan blade.
  • the fan blade extends radially outwardly from the relatively flat platform. Discontinuities between surfaces of the platform and surfaces of the fan blade create turbulence as fluids flow therepast.
  • the industry is always receptive to new devices and methods that can potentially improve efficiencies of gas turbine engines.
  • the platform includes at least one body defining a surface and having an opening receptive to a blade, a protrusion extending outwardly from the surface in a direction that will position the protrusion along a leading edge near a root of the blade.
  • the at least one body is two bodies each having an opening such that the two bodies can attach to one another and the openings form a continuous border that surrounds the blade.
  • the two bodies are detachable from one another to allow them to be replaced.
  • the protrusion has a curved surface that blends into the surface of the at least one body.
  • the protrusion serves as a fairing for the blade.
  • the at least one body is made of at least one of a composite, a polymeric material, and a metal.
  • the material of the at least one body is more resilient than that of the blade.
  • the at least one body seals to the blade.
  • the protrusion improves aerodynamic flow at the root leading edge of the blade in comparison to a platform that does not include the protrusion.
  • the improved aerodynamics allows the root leading edge of the blade to be thicker without sacrificing performance of a gas turbine engine employing the gas turbine fan fairing platform.
  • the protrusion protects the root leading edge of the blade from being contacted directly with a foreign body.
  • the method includes positioning a platform having a protrusion near an opening in at least one body of the platform such that the protrusion is adjacent a root leading edge of the fan blade.
  • FIG. 1 depicts a perspective view of a gas turbine fan fairing platform disclosed herein;
  • FIG. 2 depicts a perspective view of the turbine fan fairing platform of FIG. 1 positioned around a fan blade;
  • FIG. 3 depicts an alternate perspective view of the turbine fan fairing platform of FIG. 1 positioned around a fan blade;
  • FIG. 4 depicts a plurality of the turbine fan fairing platforms of FIG. 1 positioned around a plurality of fan blades in relative positions as they might appear on a gas turbine engine;
  • FIG. 5 schematically illustrates a gas turbine engine employing the gas turbine fan fairing platform of FIG. 1 .
  • the platform 10 includes at least one body 14 , 18 , with two of the bodies being shown in the illustrated embodiment, although any practical number of the bodies could be employed.
  • a seam 20 shows where the two bodies 14 , 18 are come together.
  • Other embodiments can have one or more seams oriented in other directions depending upon the number of bodies employed and the direction in which they come together.
  • At least one of the bodies 14 has an opening 26 receptive to a blade 30 (not shown in FIG. 1 ) and defines a surface 22 .
  • a protrusion 34 extends outward from the surface 22 in a direction that positions the protrusion 34 proximate a leading edge 38 of the blade 30 near a root 42 of the blade 30 .
  • the two bodies 14 , 18 of the platform 10 are attachable such that the opening 26 in the body 14 and an opening 46 in the body 18 form a single larger opening 50 when the bodies 14 and 18 are attached.
  • the opening 50 is sized and shaped to fit around the blade 30 near the root 42 and form a continuous border 48 that surrounds the blade 30 .
  • the two bodies 14 , 18 are also detachable from one another to allow for replacement in the event that they become damaged, for example.
  • the protrusion 34 has a curved surface 54 that blends into the surface 22 of the body 14 .
  • the protrusion 34 serves as a fairing for the blade 30 and creates a smooth aerodynamic transition between the surface 22 and the blade 30 that is an improvement in comparison to a platform that does not include the protrusion 34 .
  • the shape of the surface 54 , the protrusion 34 and surface 22 are designed to provide a smooth aerodynamic transition and consequently may have rather complex geometry.
  • the body 14 may be made of a composite or polymeric material to facilitate fabrication of the complex geometry through injection molding, for example. Alternatively, metals such as steel, titanium and aluminum could also be used.
  • the body 14 could also be made of a combination of two or more of the foregoing materials. The needs of each application can influence what material to use. Some applications may favor a lighter material while others a stronger more durable material.
  • the improved aerodynamics provided by the protrusion 34 allows the root leading edge 38 of the blade 30 to be thicker without sacrificing performance of a gas turbine engine 110 (in FIG. 5 only) employing the gas turbine fairing platform 10 .
  • Increased thickness of the root leading edge 38 of the blade 30 makes the blade 30 more durable and less prone to damage when struck since the stress concentration that naturally occurs at the root 42 is lessened by the increased thickness.
  • the thicker blade 30 can be stiffer thereby changing the vibrational modes in a direction that should lessen noise and potential damage associated with vibrating at vibrational modes associated with a thinner blade.
  • the protrusion 34 protects the root leading edge 38 of the blade 30 from being contacted directly with a foreign body.
  • the body 14 can dampen impact from strikes of foreign objects against the protrusion 34 .
  • the resiliency of the body 14 can also allow it to act as a seal to the blade 30 and to other structures near the blade 30 such as a nosecone or spinner (not shown) for example.
  • the foregoing structure allows an operator a method of faring the root leading edge 38 of the fan blade 30 of the gas turbine engine 110 by positioning the platform 10 such that the protrusion 34 is adjacent the root leading edge 38 of the fan blade 30 .
  • the word fairing is being used as a verb to describe improving aerodynamics of whatever the fairing is being done to, which in this case is the root leading edge 38 of the fan blade 30 .
  • the method also allows the operator to seal the platform 10 to the fan blade 30 as well as to isolate the root leading edge 38 of the fan blade 30 from being struck by objects directly.
  • FIG. 5 schematically illustrates a gas turbine engine 110 that can be used to power an aircraft the engine 110 is attached to (not shown), for example.
  • the gas turbine engine 110 is disclosed herein as a two-spool turbofan that generally incorporates a fan section 122 , a compressor section 124 , a combustor section 126 and a turbine section 128 .
  • the fan section 122 drives air along a bypass flowpath while the compressor section 124 drives air along a core flowpath for compression and communication into the combustor section 126 then expansion through the turbine section 128 .
  • turbofan gas turbine engine in the disclosed non-limiting embodiment, it should be understood that the concepts described herein are not limited to use with turbofans as the teachings may be applied to other types of turbine engines including three-spool architectures and even stationary non-vehicle engines.
  • gas turbine fan fairing platform 10 disclosed herein is positioned about the fan blade 30 adjacent a nose cone 130 .

Abstract

A gas turbine fan fairing platform includes at least one body defining a surface and having an opening receptive to a blade, a protrusion extending outwardly from the surface in a direction that will position the protrusion along a leading edge near a root of the blade.

Description

    BACKGROUND
  • Gas turbine engines typically include platforms near a root of a fan blade. The fan blade extends radially outwardly from the relatively flat platform. Discontinuities between surfaces of the platform and surfaces of the fan blade create turbulence as fluids flow therepast. The industry is always receptive to new devices and methods that can potentially improve efficiencies of gas turbine engines.
    • BRIEF DESCRIPTION
  • Disclosed herein is a gas turbine fan fairing platform. The platform includes at least one body defining a surface and having an opening receptive to a blade, a protrusion extending outwardly from the surface in a direction that will position the protrusion along a leading edge near a root of the blade.
  • In addition to one or more of the features described above, or as an alternative, in further embodiments the at least one body is two bodies each having an opening such that the two bodies can attach to one another and the openings form a continuous border that surrounds the blade.
  • In addition to one or more of the features described above, or as an alternative, in further embodiments the two bodies are detachable from one another to allow them to be replaced.
  • In addition to one or more of the features described above, or as an alternative, in further embodiments the protrusion has a curved surface that blends into the surface of the at least one body.
  • In addition to one or more of the features described above, or as an alternative, in further embodiments the protrusion serves as a fairing for the blade.
  • In addition to one or more of the features described above, or as an alternative, in further embodiments the at least one body is made of at least one of a composite, a polymeric material, and a metal.
  • In addition to one or more of the features described above, or as an alternative, in further embodiments the material of the at least one body is more resilient than that of the blade.
  • In addition to one or more of the features described above, or as an alternative, in further embodiments the at least one body seals to the blade.
  • In addition to one or more of the features described above, or as an alternative, in further embodiments the protrusion improves aerodynamic flow at the root leading edge of the blade in comparison to a platform that does not include the protrusion.
  • In addition to one or more of the features described above, or as an alternative, in further embodiments the improved aerodynamics allows the root leading edge of the blade to be thicker without sacrificing performance of a gas turbine engine employing the gas turbine fan fairing platform.
  • In addition to one or more of the features described above, or as an alternative, in further embodiments the protrusion protects the root leading edge of the blade from being contacted directly with a foreign body.
  • Further disclosed herein is a method of fairing a root leading edge of a fan blade of a gas turbine engine. The method includes positioning a platform having a protrusion near an opening in at least one body of the platform such that the protrusion is adjacent a root leading edge of the fan blade.
  • In addition to one or more of the features described above, or as an alternative, in further embodiments sealing the platform to the fan blade.
  • In addition to one or more of the features described above, or as an alternative, in further embodiments isolating the root leading edge of the fan blade from being struck by objects directly.
    • BRIEF DESCRIPTION OF THE DRAWINGS
  • The subject matter which is regarded as the present disclosure is particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The foregoing and other features, and advantages of the present disclosure are apparent from the following detailed description taken in conjunction with the accompanying drawings in which:
  • FIG. 1 depicts a perspective view of a gas turbine fan fairing platform disclosed herein;
  • FIG. 2 depicts a perspective view of the turbine fan fairing platform of FIG. 1 positioned around a fan blade;
  • FIG. 3 depicts an alternate perspective view of the turbine fan fairing platform of FIG. 1 positioned around a fan blade;
  • FIG. 4 depicts a plurality of the turbine fan fairing platforms of FIG. 1 positioned around a plurality of fan blades in relative positions as they might appear on a gas turbine engine; and
  • FIG. 5 schematically illustrates a gas turbine engine employing the gas turbine fan fairing platform of FIG. 1.
    •  DETAILED DESCRIPTION
  • Referring to FIGS. 1-4, an embodiment of a gas turbine fan fairing platform disclosed herein is illustrated generally at 10. The platform 10 includes at least one body 14, 18, with two of the bodies being shown in the illustrated embodiment, although any practical number of the bodies could be employed. A seam 20 shows where the two bodies 14, 18 are come together. Other embodiments can have one or more seams oriented in other directions depending upon the number of bodies employed and the direction in which they come together. At least one of the bodies 14 has an opening 26 receptive to a blade 30 (not shown in FIG. 1) and defines a surface 22. A protrusion 34 extends outward from the surface 22 in a direction that positions the protrusion 34 proximate a leading edge 38 of the blade 30 near a root 42 of the blade 30.
  • The two bodies 14, 18 of the platform 10 are attachable such that the opening 26 in the body 14 and an opening 46 in the body 18 form a single larger opening 50 when the bodies 14 and 18 are attached. The opening 50 is sized and shaped to fit around the blade 30 near the root 42 and form a continuous border 48 that surrounds the blade 30. The two bodies 14, 18 are also detachable from one another to allow for replacement in the event that they become damaged, for example.
  • The protrusion 34 has a curved surface 54 that blends into the surface 22 of the body 14. The protrusion 34 serves as a fairing for the blade 30 and creates a smooth aerodynamic transition between the surface 22 and the blade 30 that is an improvement in comparison to a platform that does not include the protrusion 34. The shape of the surface 54, the protrusion 34 and surface 22 are designed to provide a smooth aerodynamic transition and consequently may have rather complex geometry. The body 14 may be made of a composite or polymeric material to facilitate fabrication of the complex geometry through injection molding, for example. Alternatively, metals such as steel, titanium and aluminum could also be used. The body 14 could also be made of a combination of two or more of the foregoing materials. The needs of each application can influence what material to use. Some applications may favor a lighter material while others a stronger more durable material.
  • The improved aerodynamics provided by the protrusion 34 allows the root leading edge 38 of the blade 30 to be thicker without sacrificing performance of a gas turbine engine 110 (in FIG. 5 only) employing the gas turbine fairing platform 10. Increased thickness of the root leading edge 38 of the blade 30 makes the blade 30 more durable and less prone to damage when struck since the stress concentration that naturally occurs at the root 42 is lessened by the increased thickness. Additionally, the thicker blade 30 can be stiffer thereby changing the vibrational modes in a direction that should lessen noise and potential damage associated with vibrating at vibrational modes associated with a thinner blade. Furthermore, the protrusion 34 protects the root leading edge 38 of the blade 30 from being contacted directly with a foreign body. And since the material of the body 14 is in some embodiments more resilient than the blade 30 the body 14 can dampen impact from strikes of foreign objects against the protrusion 34. The resiliency of the body 14 can also allow it to act as a seal to the blade 30 and to other structures near the blade 30 such as a nosecone or spinner (not shown) for example.
  • The foregoing structure allows an operator a method of faring the root leading edge 38 of the fan blade 30 of the gas turbine engine 110 by positioning the platform 10 such that the protrusion 34 is adjacent the root leading edge 38 of the fan blade 30. In this context the word fairing is being used as a verb to describe improving aerodynamics of whatever the fairing is being done to, which in this case is the root leading edge 38 of the fan blade 30. The method also allows the operator to seal the platform 10 to the fan blade 30 as well as to isolate the root leading edge 38 of the fan blade 30 from being struck by objects directly.
  • FIG. 5 schematically illustrates a gas turbine engine 110 that can be used to power an aircraft the engine 110 is attached to (not shown), for example. The gas turbine engine 110 is disclosed herein as a two-spool turbofan that generally incorporates a fan section 122, a compressor section 124, a combustor section 126 and a turbine section 128. The fan section 122 drives air along a bypass flowpath while the compressor section 124 drives air along a core flowpath for compression and communication into the combustor section 126 then expansion through the turbine section 128. Although depicted as a turbofan gas turbine engine in the disclosed non-limiting embodiment, it should be understood that the concepts described herein are not limited to use with turbofans as the teachings may be applied to other types of turbine engines including three-spool architectures and even stationary non-vehicle engines. In one embodiment the gas turbine fan fairing platform 10 disclosed herein is positioned about the fan blade 30 adjacent a nose cone 130.
  • While the present disclosure has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the present disclosure is not limited to such disclosed embodiments. Rather, the present disclosure can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the spirit and scope of the present disclosure. Additionally, while various embodiments of the present disclosure have been described, it is to be understood that aspects of the present disclosure may include only some of the described embodiments. Accordingly, the present disclosure is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.

Claims (14)

1. A gas turbine fan fairing platform comprising at least one body defining a surface and having an opening receptive to a blade, a protrusion extending outwardly from the surface in a direction that will position the protrusion along a leading edge near a root of the blade.
2. The gas turbine fan fairing platform of claim 1, wherein the at least one body is two bodies each having an opening such that the two bodies can attach to one another and the openings form a continuous border that surrounds the blade.
3. The gas turbine fan fairing platform of claim 1, wherein the two bodies are detachable from one another to allow them to be replaced.
4. The gas turbine fan fairing platform of claim 1, wherein the protrusion has a curved surface that blends into the surface of the at least one body.
5. The gas turbine fan fairing platform of claim 1, wherein the protrusion serves as a fairing for the blade.
6. The gas turbine fan fairing platform of claim 1, wherein the at least one body is made of at least one of a composite, a polymeric material, and a metal.
7. The gas turbine fan fairing platform of claim 1, wherein the material of the body is more resilient than that of the blade.
8. The gas turbine fan fairing platform of claim 1, wherein the at least one body seals to the blade.
9. The gas turbine fan fairing platform of claim 1, wherein the protrusion improves aerodynamic flow at the root leading edge of the blade in comparison to a platform that does not include the protrusion.
10. The gas turbine fan fairing platform of claim 9, wherein the improved aerodynamics allows the root leading edge of the blade to be thicker without sacrificing performance of a gas turbine engine employing the gas turbine fan fairing platform.
11. The gas turbine fan fairing platform of claim 1, wherein the protrusion protects the root leading edge of the blade from being contacted directly with a foreign body.
12. A method of fairing a root leading edge of a fan blade of a gas turbine engine, comprising positioning a platform having a protrusion near an opening in at least one body of the platform such that the protrusion is adjacent a root leading edge of the fan blade.
13. The method of fairing a root leading edge of a fan blade of a gas turbine engine of claim 12, further comprising sealing the platform to the fan blade.
14. The method of fairing a root leading edge of a fan blade of a gas turbine engine of claim 12, further comprising isolating the root leading edge of the fan blade from being struck by objects directly.
US14/841,852 2015-09-01 2015-09-01 Gas turbine fan fairing platform and method of fairing a root leading edge of a fan blade of a gas turbine engine Abandoned US20170058916A1 (en)

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EP16186865.8A EP3139005B1 (en) 2015-09-01 2016-09-01 Gas turbine fan fairing platform and method of fairing a root leading edge of a fan blade of a gas turbine engine

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US20170218969A1 (en) * 2014-07-31 2017-08-03 Ksb Aktiengesellschaft Flow-Conducting Component
US20170320159A1 (en) * 2016-02-16 2017-11-09 Rolls-Royce Plc Manufacture of a drum for a gas turbine engine
FR3070420A1 (en) * 2017-08-23 2019-03-01 Safran Aircraft Engines HUB COVER FOR AERO-ACOUSTIC STRUCTURE

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