US20120237351A1 - Retention for bonded hollow fan blade cover - Google Patents

Retention for bonded hollow fan blade cover Download PDF

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Publication number
US20120237351A1
US20120237351A1 US13/050,275 US201113050275A US2012237351A1 US 20120237351 A1 US20120237351 A1 US 20120237351A1 US 201113050275 A US201113050275 A US 201113050275A US 2012237351 A1 US2012237351 A1 US 2012237351A1
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US
United States
Prior art keywords
airfoil
pressure side
trench
suction side
contour
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.)
Abandoned
Application number
US13/050,275
Inventor
Michael A. Weisse
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.)
RTX Corp
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to US13/050,275 priority Critical patent/US20120237351A1/en
Assigned to UNITED TECHNOLOGIES CORPORATION reassignment UNITED TECHNOLOGIES CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: WEISSE, MICHAEL A.
Priority to EP12159600.1A priority patent/EP2500263B1/en
Publication of US20120237351A1 publication Critical patent/US20120237351A1/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

    • 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
    • B64C11/16—Blades
    • B64C11/20—Constructional features
    • B64C11/24—Hollow 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • 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
    • 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
    • F04D29/26—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

Definitions

  • This invention relates to improvements in hollow metal propellers and fan blades adapted primarily for use in aviation service.
  • propeller and fan blades may be hollow and have stiffening ribs disposed therein.
  • the ribs are typically welded to one plate or the other, or to a propeller shaft.
  • a two part airfoil has a suction side, a pressure side, a rib extending from one of the pressure side or the second side, the rib having a groove therein, and a riblet extending from an other of the pressure side or the suction side, the riblet fitting within the groove.
  • a two-part airfoil includes a suction side, a pressure side, a rib extending from one of the pressure side or the second side and having a groove therein.
  • the groove has a first contour and a riblet extending from an other of the pressure side or the suction side has a second contour fitting within the first contour of the groove such that an effect of tear and shear force affecting said suction side and said pressure side are lessened .
  • FIG. 1 shows a prior art reinforcing rib of an airfoil attached to a cover of an airfoil.
  • FIG. 2 shows an embodiment of a reinforcing rib of an airfoil attached to a cover of an airfoil.
  • FIG. 3 shows an airfoil incorporating the ribs of FIG. 2 .
  • FIG. 4 shows a top view of the air foil of FIG. 3 .
  • FIG. 1 a prior art view of a two-part airfoil 10 is shown.
  • the airfoil 10 has a suction side cover 15 and a pressure side 20 .
  • the suction side cover 15 is attached to a rib 25 depending from an inside 23 of the pressure side 20 .
  • the rib is attached to the suction side cover 15 by a bond 30 such as glue, welding or the like.
  • the airfoil 110 has a suction side cover 115 and a pressure side 120 .
  • the pressure side 120 has an inner surface 127 from which ribs 125 extend towards the suction side cover 115 .
  • the ribs 125 have a longitudinal groove 128 formed therein.
  • the suction side cover 115 has plurality of riblets 130 extending from an inner surface 131 thereof towards the pressure side 120 .
  • the groove may be machined or cast or forged into the ribs 125 .
  • groove 128 is shown with a rectangular contour and the riblets 130 also have a rectangular contour, other mating riblet 130 contours and groove 128 contours are contemplated herein providing such other contours provide increased gluing area and less motion between a riblet 130 and the groove 128 .
  • a glue 133 such as an epoxy or a urethane, may be used to join the ribs 125 and the riblets 130 together within the groove 128 .
  • glue 133 such as an epoxy or a urethane
  • the amount of glue 133 used to join the suction side cover 115 and the pressure side 120 is increased by the amount of glue 133 placed on the sides 135 of the riblet, as compared to the prior art.
  • the added glue 133 provides a concomitantly stronger bond between the suction side cover 115 and the suction side 120 .
  • the urethane glue may provide damping between the suction side cover 115 and the pressure side 120
  • the effect of operative forces which may cause shear and tearing motion between the suction side cover 115 and the pressure side 120 , are minimized because of a mechanical bond between the ribs 125 and the riblets 130 as the suction side cover 115 and pressure side 120 react to operation within an airstream.
  • This mechanical advantage minimizes the effect of tear and shear force affecting suction side cover 115 and pressure side 120 of the airfoil 110 .
  • the inner surface 127 of the pressure side has an trench 140 (see FIG. 4 ) that approximates the sides 145 and the bottom 147 of the elbow-shape of the suction side cover 115 .
  • the trench is spaced from the leading edge 154 and the trailing edge 150 and the base 160 of the airfoil 110 .
  • the pressure side 115 has a first plurality 165 of ribs 125 extending from the trench 140 near the base 160 to the trench 140 adjacent the leading edge 154 of the trench and a second plurality 175 of ribs 125 extending from the trench 140 near the trailing edge 150 to the trench 140 near the leading edge 154 .
  • the suction side cover 115 has a set of corresponding riblets 130 that fit within the grooves of the first plurality 165 of ribs 125 and the second plurality 170 of ribs 125 .
  • the second plurality of ribs 170 extend from near the trailing 150 to near the leading edge 154 or towards the blade tip 173 .
  • the suction side cover 115 has a bead 180 extending along its outside edge 185 that mates with the trench 140 .
  • glue 133 is placed in the grooves 128 in the ribs 125 and the trench 140 and the riblets 130 are pressed into the grooves 128 and the bead 180 is pressed into the trench 140 .
  • a system designed according to an embodiment of this disclosure will not necessarily include all of the features shown in any one of the Figures or all of the portions schematically shown in the Figures.
  • selected features of one example embodiment may be combined with selected features of other example embodiments.
  • the riblets 130 may be attached to the pressure side 115 and the ribs 125 may be attached to the cover 120 .

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

Abstract

A two part airfoil has a suction side, a pressure side, a rib extending from one of the pressure side or the second side, the rib having a groove therein, and a riblet extending from an other of the pressure side or the suction side, the riblet fitting within the groove.

Description

    BACKGROUND
  • This invention relates to improvements in hollow metal propellers and fan blades adapted primarily for use in aviation service.
  • It is well known that propeller and fan blades may be hollow and have stiffening ribs disposed therein. The ribs are typically welded to one plate or the other, or to a propeller shaft.
    • SUMMARY
  • According to an embodiment disclosed herein, a two part airfoil has a suction side, a pressure side, a rib extending from one of the pressure side or the second side, the rib having a groove therein, and a riblet extending from an other of the pressure side or the suction side, the riblet fitting within the groove.
  • According to a further embodiment disclosed herein, a two-part airfoil includes a suction side, a pressure side, a rib extending from one of the pressure side or the second side and having a groove therein. The groove has a first contour and a riblet extending from an other of the pressure side or the suction side has a second contour fitting within the first contour of the groove such that an effect of tear and shear force affecting said suction side and said pressure side are lessened .
    • BRIEF DESCRIPTION OF THE DRAWINGS
  • The various features and advantages of the disclosed examples will become apparent to those skilled in the art from the following detailed description. The drawings that accompany the detailed description can be briefly described as follows.
  • FIG. 1 shows a prior art reinforcing rib of an airfoil attached to a cover of an airfoil.
  • FIG. 2 shows an embodiment of a reinforcing rib of an airfoil attached to a cover of an airfoil.
  • FIG. 3 shows an airfoil incorporating the ribs of FIG. 2.
  • FIG. 4 shows a top view of the air foil of FIG. 3.
    •  DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT
  • Referring to FIG. 1, a prior art view of a two-part airfoil 10 is shown. The airfoil 10 has a suction side cover 15 and a pressure side 20. The suction side cover 15 is attached to a rib 25 depending from an inside 23 of the pressure side 20. The rib is attached to the suction side cover 15 by a bond 30 such as glue, welding or the like.
  • Referring now to FIGS. 2 and 3, an airfoil 110 is shown. The airfoil 110 has a suction side cover 115 and a pressure side 120. The pressure side 120 has an inner surface 127 from which ribs 125 extend towards the suction side cover 115. The ribs 125 have a longitudinal groove 128 formed therein. The suction side cover 115 has plurality of riblets 130 extending from an inner surface 131 thereof towards the pressure side 120. The groove may be machined or cast or forged into the ribs 125. Though the groove 128 is shown with a rectangular contour and the riblets 130 also have a rectangular contour, other mating riblet 130 contours and groove 128 contours are contemplated herein providing such other contours provide increased gluing area and less motion between a riblet 130 and the groove 128.
  • A glue 133, such as an epoxy or a urethane, may be used to join the ribs 125 and the riblets 130 together within the groove 128. One can see that, by joining the ribs 125 and the riblets 130 together within the groove 128, the amount of glue 133 used to join the suction side cover 115 and the pressure side 120 is increased by the amount of glue 133 placed on the sides 135 of the riblet, as compared to the prior art. The added glue 133 provides a concomitantly stronger bond between the suction side cover 115 and the suction side 120. If a urethane glue is used, the urethane glue may provide damping between the suction side cover 115 and the pressure side 120
  • Moreover, by placing the riblet 130 within the groove 128, the effect of operative forces, which may cause shear and tearing motion between the suction side cover 115 and the pressure side 120, are minimized because of a mechanical bond between the ribs 125 and the riblets 130 as the suction side cover 115 and pressure side 120 react to operation within an airstream. This mechanical advantage minimizes the effect of tear and shear force affecting suction side cover 115 and pressure side 120 of the airfoil 110.
  • Referring now to FIGS. 3 and 4, an interior view of the suction side cover 115 and the pressure side 120 are shown. The inner surface 127 of the pressure side has an trench 140 (see FIG. 4) that approximates the sides 145 and the bottom 147 of the elbow-shape of the suction side cover 115. The trench is spaced from the leading edge 154 and the trailing edge 150 and the base 160 of the airfoil 110. The pressure side 115 has a first plurality 165 of ribs 125 extending from the trench 140 near the base 160 to the trench 140 adjacent the leading edge 154 of the trench and a second plurality 175 of ribs 125 extending from the trench 140 near the trailing edge 150 to the trench 140 near the leading edge 154.
  • The suction side cover 115 has a set of corresponding riblets 130 that fit within the grooves of the first plurality 165 of ribs 125 and the second plurality 170 of ribs 125. The second plurality of ribs 170 extend from near the trailing 150 to near the leading edge 154 or towards the blade tip 173. The suction side cover 115 has a bead 180 extending along its outside edge 185 that mates with the trench 140.
  • To construct the airfoil, glue 133 is placed in the grooves 128 in the ribs 125 and the trench 140 and the riblets 130 are pressed into the grooves 128 and the bead 180 is pressed into the trench 140.
  • Although a combination of features is shown in the illustrated examples, not all of them need to be combined to realize the benefits of various embodiments of this disclosure. In other words, a system designed according to an embodiment of this disclosure will not necessarily include all of the features shown in any one of the Figures or all of the portions schematically shown in the Figures. Moreover, selected features of one example embodiment may be combined with selected features of other example embodiments. For instance, the riblets 130 may be attached to the pressure side 115 and the ribs 125 may be attached to the cover 120.
  • The preceding description is exemplary rather than limiting in nature. Variations and modifications to the disclosed examples may become apparent to those skilled in the art that do not necessarily depart from the essence of this disclosure. The scope of legal protection given to this disclosure can only be determined by studying the following claims.

Claims (18)

1. A two part airfoil comprising:
a suction side,
a pressure side,
a rib extending from one of said pressure side or said second side, said rib having a groove therein, and
a riblet extending from an other of said pressure side or said suction side, said riblet fitting within said groove.
2. The two part airfoil of claim 1 further comprising:
a glue disposed between said rib and said riblets wherein motion between said suction side and said pressure side is damped.
3. The two part airfoil of claim 2 wherein said glue is a urethane glue.
4. The two part airfoil of claim 1 wherein said groove is longitudinal.
5. The two part airfoil of claim 1 wherein one of said suction side and said pressure side has a trench adjacent an outer profile thereof and wherein an other of said suction side and said pressure side has a bead that fits in said trench.
6. The two part airfoil of claim 5 wherein said trench is adjacent a leading edge and a trailing edge of said airfoil.
7. The two part airfoil of claim 5 wherein said trench is adjacent a leading edge and a base of said airfoil.
8. The two part airfoil of claim 7 wherein a rib extends from said trench adjacent a base of said airfoil to said trench adjacent a leading edge of said airfoil.
9. The two part airfoil of claim 8 wherein said trench is adjacent a leading edge and a trailing edge of said airfoil.
10. The two part airfoil of claim 9 wherein a rib extends from said trench adjacent said leading edge to said trench adjacent said trailing edge.
11. The two part airfoil of claim 5 wherein said trench is in said pressure side.
12. The two part airfoil of claim 1 wherein said rib extends from said pressure side.
13. The two part airfoil of claim 1 wherein said riblet extends from said suction side.
14. A two-part airfoil comprising:
a suction side,
a pressure side,
a rib extending from one of said pressure side or said second side, said rib having a groove therein said groove having a first contour, and
a riblet extending from an other of said pressure side or said suction side, said riblet having a second contour fitting within said first contour of said groove such that an effect of tear and shear force affecting said suction side and said pressure side are lessened.
15. The two-part airfoil of claim 14 wherein said first contour and said second contour mate.
16. The two-part airfoil of claim 14 wherein said first contour and said second contour are rectangular.
17. The two part airfoil of claim 14 further comprising:
a glue disposed between said first contour and said second contour wherein motion between said suction side and said pressure side is damped.
18. The two part airfoil of claim 17 wherein said glue is a urethane glue.
US13/050,275 2011-03-17 2011-03-17 Retention for bonded hollow fan blade cover Abandoned US20120237351A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US13/050,275 US20120237351A1 (en) 2011-03-17 2011-03-17 Retention for bonded hollow fan blade cover
EP12159600.1A EP2500263B1 (en) 2011-03-17 2012-03-15 Improved retention for bonded hollow fan blade cover

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Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014051670A1 (en) * 2012-09-25 2014-04-03 United Technologies Corporation Airfoil array with airfoils that differ in geometry according to geometry classes
US20140227100A1 (en) * 2011-09-23 2014-08-14 Howden Solyvent-Ventect Rotating Machine Blade with Reinforced Modular Structure
WO2015102691A3 (en) * 2013-11-26 2015-09-17 United Technologies Corporation Fan blade with integrated composite fan blade cover
US20180030995A1 (en) * 2016-08-01 2018-02-01 United Technologies Corporation Fan blade with composite cover
US20180038386A1 (en) * 2016-08-08 2018-02-08 United Technologies Corporation Fan blade with composite cover
EP3318717A1 (en) * 2016-11-08 2018-05-09 Rolls-Royce Corporation Undercut on airfoil coversheet support member
EP3734014A1 (en) * 2019-05-01 2020-11-04 Raytheon Technologies Corporation Welding method for hollow airfoils and intermediate body
US11225874B2 (en) 2019-12-20 2022-01-18 Raytheon Technologies Corporation Turbine engine rotor blade with castellated tip surface
CN115489719A (en) * 2022-10-28 2022-12-20 四川腾盾科技有限公司 Aircraft wing rudder surface structure
CN116336007A (en) * 2021-12-23 2023-06-27 通用电气公司 Integrated Stator-Fan Frame Assembly
EP4219902A1 (en) * 2016-09-14 2023-08-02 Raytheon Technologies Corporation Fan blade with structural spar and integrated leading edge
US20240200458A1 (en) * 2022-12-20 2024-06-20 Rtx Corporation Hollow airfoil construction using cover subassembly
US20240240565A1 (en) * 2021-12-08 2024-07-18 General Electric Company Cover plate connections for a hollow fan blade

Families Citing this family (4)

* Cited by examiner, † Cited by third party
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US20130078103A1 (en) * 2011-09-23 2013-03-28 Christopher S. McKaveney Hollow fan blade rib geometry
US10329918B2 (en) 2013-10-18 2019-06-25 United Technologies Corporation Multiple piece engine component
US10443613B2 (en) 2017-05-31 2019-10-15 United Technologies Corporation Hollow fan blade with structural ribs
FR3105291B1 (en) * 2019-12-20 2023-03-10 Safran Aircraft Engines FAN OR PROPELLER BLADE FOR AN AIRCRAFT TURBOMACHINE AND METHOD FOR MANUFACTURING THEREOF

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5269058A (en) * 1992-12-16 1993-12-14 General Electric Company Design and processing method for manufacturing hollow airfoils
US5487930A (en) * 1991-10-03 1996-01-30 Tolo, Inc. Three structure structural element with interlocking ribbing
US7037568B1 (en) * 2003-07-15 2006-05-02 Rogers Terry W Joining member for mechanically joining a skin to a supporting rib
US7189064B2 (en) * 2004-05-14 2007-03-13 General Electric Company Friction stir welded hollow airfoils and method therefor
US7238409B1 (en) * 2002-05-23 2007-07-03 Rohr, Inc. Structural element with rib-receiving member
US7625623B2 (en) * 2005-05-25 2009-12-01 The Boeing Company Joints formed by joining structures
US20100266415A1 (en) * 2009-04-16 2010-10-21 United Technologies Corporation Hybrid structure fan blade
US20120034093A1 (en) * 2010-08-06 2012-02-09 Rohr, Inc. Blade
US8585368B2 (en) * 2009-04-16 2013-11-19 United Technologies Corporation Hybrid structure airfoil

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2954208A (en) * 1953-01-09 1960-09-27 Gen Motors Corp Air foil section
US5498137A (en) * 1995-02-17 1996-03-12 United Technologies Corporation Turbine engine rotor blade vibration damping device
US5849393A (en) * 1997-04-17 1998-12-15 Mcdonnell Douglas Corporation Structural element and method of making
US20030069321A1 (en) * 2001-10-05 2003-04-10 Lin Wendy Wen-Ling High modulus, impact resistant foams for structural components
US20050247756A1 (en) * 2004-03-31 2005-11-10 Frazer James T Connection mechanism and method
US7398586B2 (en) * 2005-11-01 2008-07-15 The Boeing Company Methods and systems for manufacturing a family of aircraft wings and other composite structures
US7980817B2 (en) * 2007-04-16 2011-07-19 United Technologies Corporation Gas turbine engine vane
US8235670B2 (en) * 2009-06-17 2012-08-07 Siemens Energy, Inc. Interlocked CMC airfoil

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5487930A (en) * 1991-10-03 1996-01-30 Tolo, Inc. Three structure structural element with interlocking ribbing
US5269058A (en) * 1992-12-16 1993-12-14 General Electric Company Design and processing method for manufacturing hollow airfoils
US7238409B1 (en) * 2002-05-23 2007-07-03 Rohr, Inc. Structural element with rib-receiving member
US7037568B1 (en) * 2003-07-15 2006-05-02 Rogers Terry W Joining member for mechanically joining a skin to a supporting rib
US7189064B2 (en) * 2004-05-14 2007-03-13 General Electric Company Friction stir welded hollow airfoils and method therefor
US7625623B2 (en) * 2005-05-25 2009-12-01 The Boeing Company Joints formed by joining structures
US20100266415A1 (en) * 2009-04-16 2010-10-21 United Technologies Corporation Hybrid structure fan blade
US8585368B2 (en) * 2009-04-16 2013-11-19 United Technologies Corporation Hybrid structure airfoil
US20120034093A1 (en) * 2010-08-06 2012-02-09 Rohr, Inc. Blade

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140227100A1 (en) * 2011-09-23 2014-08-14 Howden Solyvent-Ventect Rotating Machine Blade with Reinforced Modular Structure
US10408060B2 (en) * 2011-09-23 2019-09-10 Howden Solyvent-Ventec Rotating machine blade with reinforced modular structure
WO2014051670A1 (en) * 2012-09-25 2014-04-03 United Technologies Corporation Airfoil array with airfoils that differ in geometry according to geometry classes
EP3653838A1 (en) * 2012-09-25 2020-05-20 United Technologies Corporation Airfoil array with airfoils that differ in geometry and include mistake-proof features
US10047609B2 (en) 2012-09-25 2018-08-14 United Technologies Corporation Airfoil array with airfoils that differ in geometry according to geometry classes
US10337521B2 (en) 2013-11-26 2019-07-02 United Technologies Corporation Fan blade with integrated composite fan blade cover
WO2015102691A3 (en) * 2013-11-26 2015-09-17 United Technologies Corporation Fan blade with integrated composite fan blade cover
US11396884B2 (en) 2016-08-01 2022-07-26 Raytheon Technologies Corporation Fan blade with composite cover
US10570917B2 (en) * 2016-08-01 2020-02-25 United Technologies Corporation Fan blade with composite cover
US20180030995A1 (en) * 2016-08-01 2018-02-01 United Technologies Corporation Fan blade with composite cover
US20180038386A1 (en) * 2016-08-08 2018-02-08 United Technologies Corporation Fan blade with composite cover
EP4219902A1 (en) * 2016-09-14 2023-08-02 Raytheon Technologies Corporation Fan blade with structural spar and integrated leading edge
EP3318717A1 (en) * 2016-11-08 2018-05-09 Rolls-Royce Corporation Undercut on airfoil coversheet support member
US10450872B2 (en) 2016-11-08 2019-10-22 Rolls-Royce Corporation Undercut on airfoil coversheet support member
US11389900B2 (en) 2019-05-01 2022-07-19 Raytheon Technologies Corporation Welding method for hollow airfoils and intermediate body
EP3734014A1 (en) * 2019-05-01 2020-11-04 Raytheon Technologies Corporation Welding method for hollow airfoils and intermediate body
US11225874B2 (en) 2019-12-20 2022-01-18 Raytheon Technologies Corporation Turbine engine rotor blade with castellated tip surface
US20240240565A1 (en) * 2021-12-08 2024-07-18 General Electric Company Cover plate connections for a hollow fan blade
CN116336007A (en) * 2021-12-23 2023-06-27 通用电气公司 Integrated Stator-Fan Frame Assembly
CN115489719A (en) * 2022-10-28 2022-12-20 四川腾盾科技有限公司 Aircraft wing rudder surface structure
US20240200458A1 (en) * 2022-12-20 2024-06-20 Rtx Corporation Hollow airfoil construction using cover subassembly
US12055066B2 (en) * 2022-12-20 2024-08-06 Rtx Corporation Hollow airfoil construction using cover subassembly

Also Published As

Publication number Publication date
EP2500263A3 (en) 2015-11-04
EP2500263A2 (en) 2012-09-19
EP2500263B1 (en) 2020-01-22

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