[go: up one dir, main page]

US20140169972A1 - Fan with integral shroud - Google Patents

Fan with integral shroud Download PDF

Info

Publication number
US20140169972A1
US20140169972A1 US13/716,959 US201213716959A US2014169972A1 US 20140169972 A1 US20140169972 A1 US 20140169972A1 US 201213716959 A US201213716959 A US 201213716959A US 2014169972 A1 US2014169972 A1 US 2014169972A1
Authority
US
United States
Prior art keywords
shroud
fan
bladed rotor
integrally bladed
metallic
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
US13/716,959
Inventor
Gabriel L. Suciu
Jesse M. Chandler
Brian D. Merry
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
United Technologies Corp
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 United Technologies Corp filed Critical United Technologies Corp
Priority to US13/716,959 priority Critical patent/US20140169972A1/en
Assigned to UNITED TECHNOLOGIES CORPORATION reassignment UNITED TECHNOLOGIES CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: CHANDLER, JESSE M., MERRY, BRIAN D., SUCIU, GABRIEL L.
Priority to PCT/US2013/072993 priority patent/WO2014099365A1/en
Priority to EP13863829.1A priority patent/EP2932039A4/en
Publication of US20140169972A1 publication Critical patent/US20140169972A1/en
Abandoned legal-status Critical Current

Links

Images

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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • 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
    • F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
    • 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
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/53—Building or constructing in particular ways by integrally manufacturing a component, e.g. by milling from a billet or one piece construction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/12—Light metals
    • F05D2300/121—Aluminium
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/133—Titanium
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/173—Aluminium alloys, e.g. AlCuMgPb
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/174—Titanium alloys, e.g. TiAl
    • 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
    • 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
    • F05D2300/614—Fibres or filaments
    • 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

  • a method of minimizing flutter in this scenario is to use a variable area fan nozzle (“VAFN”) to change the area at the back end of the fan.
  • VAFN variable area fan nozzle
  • the VAFN can create or eliminate back pressure to get the fan out of the flutter range.
  • An integrally bladed rotor for use in a gas turbine engine includes a central hub; a plurality of airfoils extending from the central hub, each airfoil with a tip, a leading edge and a trailing edge; and a shroud with a metallic portion connecting to the tip of each airfoil to rotate with the airfoils.
  • FIG. 1A is a front view of a fan with an integral shroud in a fan casing.
  • FIG. 1B is a perspective view of the fan with integral shroud of FIG. 1A with the fan casing partially cut away.
  • FIG. 2A is a perspective view of a second embodiment of a fan with a shroud.
  • FIG. 2B is a cross-sectional view of the shroud of FIG. 2A .
  • FIG. 1A is a front view of fan 10 with an integral shroud 12 in fan casing 14 .
  • FIG. 1B is a perspective view of fan 10 with integral shroud 12 with fan casing 14 partially cut away. A partial portion of an aircraft body 16 is also shown.
  • Fan 10 is an integrally bladed rotor type fan, with hub 18 and a plurality of airfoils 20 extending radially from hub 18 . Each airfoil 20 includes tip 22 , leading edge 24 and trailing edge (not shown).
  • hub 18 , airfoils 20 and shroud 12 are formed as an integral unit. They can be formed, for example, of a metallic material, for example, aluminum or titanium (including alloys) and machined into shape desired. In alternate embodiments, shroud 12 can be formed separately and connected to integrally bladed rotor fan 10 .
  • Shroud 12 connects to tips 22 of airfoils 20 , extending from leading edge 24 to trailing edge, and rotates with airfoils 20 .
  • Shroud 12 is spaced apart from case 14 with a tight clearance, for example, 0 mm (0 inches) to 2.54 mm (0.100 inches).
  • Fan 10 acts to pull air into engine as airfoils 20 and shroud 12 spin in case 14 .
  • integrally bladed rotor fan 10 is mounted to aircraft body 16 .
  • the boundary layer of air coming into the fan can have distortions, which can lead to vibrations or flutter in airfoils 20 .
  • the minimization of flutter is desirable.
  • Shroud 12 connects to tips 22 of airfoils 20 to stabilize airfoils by providing a second connection to airfoils 20 ; the first connection being to hub 18 at the inner diameter and the second connection to shroud 12 , at outer diameter.
  • These stabilizing connections reduce the airfoil vibratory effects of fan 10 , even when receiving a turbulent airflow.
  • blade flutter due to this turbulent airflow was controlled by using a variable area fan nozzle (“VAFN”) downstream from the fan.
  • VAFN variable area fan nozzle
  • the VAFN was able to reduce flow through the fan by controlling the area at the back end of the fan, and thus increasing or decreasing back pressure. Although this was an effective way of reducing blade flutter, the VAFN is a large and heavy system which reduced efficiency of the overall engine.
  • Fan 10 with integral shroud 12 controls vibration and flutter in airfoils 20 without the need for a VAFN, reducing size and weight as compared to past systems.
  • shroud 12 can also help to eliminate some stresses in airfoils 20 as it can carry some of blade load when fan 10 is in operation.
  • Integrally formed shroud 12 will also eliminate blade tip 22 leakage in fan 10 (which can lead to loss of efficiency and potential stalls), and the tight clearance between shroud 12 and casing 14 will minimize performance losses caused by air going outside of the shroud 12 .
  • FIG. 2A is a perspective view of a second embodiment of fan 10 with hybrid shroud 32 , with part of fan casing 14 cut away
  • FIG. 2B is a cross-sectional view of shroud 32 .
  • Fan 10 is an integrally bladed rotor type fan, with hub 18 and a plurality of airfoils 20 extending radially from hub 18 .
  • Each airfoil 20 has tip 22 , leading edge 24 and trailing edge 25 .
  • Shroud 32 includes metallic portion 34 (with circumferentially curved portion 36 , first ridge 38 and second ridge 40 ) and composite portion 42 .
  • Shroud 32 metallic portion 34 connects to tips 22 of airfoils 20 , and can be formed integral to fan 10 or can be formed separate and attached to tips 22 .
  • Circumferentially curved portion 36 of shroud connects to tips 22 and extends from leading edge 24 to trailing edge 25 of airfoils 20 .
  • First flange 38 extends perpendicular from circumferentially curved portion 36 outward, away from airfoils 20 at leading edge 24 .
  • Second flange 40 extends perpendicular from circumferentially curved portion 36 outward, away from airfoils 20 at trailing edge 25 .
  • Composite portion 42 can be a composite wrap that wraps circumferentially around circumferentially curved portion 36 between first flange 38 and second flange 40 .
  • shroud 32 spins with fan 10 as fan pulls air into engine within case 14 .
  • Hybrid shroud 32 with metallic portion 34 and composite portion 42 allows for a high-strength, light-weight shroud 32 that can help stabilize airfoils 20 at outer diameter (tip 22 ) to reduce blade vibrations and flutter even when fan 10 is ingesting a very turbulent airflow.
  • Metallic portion 34 of shroud 32 can be formed integral to fan 10 airfoils 20 , ensuring high strength in connection at tips 22 , and composite portion 42 can be wrapped around to reinforce metallic portion 34 without adding a lot of additional weight.
  • Shroud 32 can also increase hoop strength of fan 10 .
  • fan 10 with integral shroud 12 , 32 reduces or eliminates vibrations or flutter in blades, eliminating the need for heavy and large VAFNs used in past systems to reduce flutter.
  • Integral shroud 12 , 32 connects to airfoil tips 22 to stabilize blade at outer diameter, thereby allowing fan 10 airfoils 20 to resist vibrations even when ingesting very turbulent airflows.
  • An integrally bladed rotor for use in a gas turbine engine includes a central hub; a plurality of airfoils extending from the central hub, each airfoil with a tip, a leading edge and a trailing edge; and a shroud with a metallic portion connecting to the tip of each airfoil to rotate with the airfoils.
  • Additional and/or alternative embodiments include the shroud being integral to the airfoils; the shroud being the same material as the airfoils; the entire shroud being metallic; the shroud comprising a metallic portion and a composite portion; the metallic portion comprising a metallic portion curved in the circumferential direction extending from the leading edge to the trailing edge of each airfoil, a first radial outward flange extending from the metallic portion at the leading edge, and a second radial outward flange extending from the metallic portion at the trailing edge; the composite portion wrapping around the metallic portion between the first radial outward flange and the second radial outward flange; a fan casing surrounding the integrally bladed rotor; the fan casing being spaced apart from the shroud with a tight clearance; the integrally bladed rotor being metallic; and/or the integrally bladed rotor being composite.
  • a fan includes an integrally bladed rotor with a plurality of blades with tips; a shroud extending around the blades and securing to the tips of each blade; and a fan casing surrounding the shroud, wherein the shroud is at least partially metallic.
  • Additional and/or alternative embodiments include the integrally bladed rotor and the shroud being entirely metallic; the integrally bladed rotor and the shroud being the same material; the integrally bladed rotor and the shroud being formed integrally; the shroud comprising a metallic portion and a composite portion; the metallic portion comprising a ring having an inner surface connected to the tips of the blades and an outer surface that includes a circumferential channel; the composite portion wrapping around the metallic portion in the circumferential channel; and/or the fan casing being spaced apart from the shroud with a tight clearance.

Landscapes

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

Abstract

An integrally bladed rotor for use in a gas turbine engine includes a central hub; a plurality of airfoils extending from the central hub, each airfoil with a tip, a leading edge and a trailing edge; and a shroud with a metallic portion connecting to the tip of each airfoil to rotate with the airfoils.

Description

    BACKGROUND
  • Fans blades in gas turbine engines are sensitive to blade vibrations or flutter. This is especially pronounced when fans have a lower pressure ratio, for example when an engine is connected directly to an aircraft body (instead of under a wing). The connection directly to the aircraft body leads to more turbulent air entering the fan. A method of minimizing flutter in this scenario is to use a variable area fan nozzle (“VAFN”) to change the area at the back end of the fan. The VAFN can create or eliminate back pressure to get the fan out of the flutter range.
    • SUMMARY
  • An integrally bladed rotor for use in a gas turbine engine includes a central hub; a plurality of airfoils extending from the central hub, each airfoil with a tip, a leading edge and a trailing edge; and a shroud with a metallic portion connecting to the tip of each airfoil to rotate with the airfoils.
    • BRIEF DESCRIPTION OF THE DRAWINGS
  • FIG. 1A is a front view of a fan with an integral shroud in a fan casing.
  • FIG. 1B is a perspective view of the fan with integral shroud of FIG. 1A with the fan casing partially cut away.
  • FIG. 2A is a perspective view of a second embodiment of a fan with a shroud.
  • FIG. 2B is a cross-sectional view of the shroud of FIG. 2A.
    •  DETAILED DESCRIPTION
  • FIG. 1A is a front view of fan 10 with an integral shroud 12 in fan casing 14. FIG. 1B is a perspective view of fan 10 with integral shroud 12 with fan casing 14 partially cut away. A partial portion of an aircraft body 16 is also shown. Fan 10 is an integrally bladed rotor type fan, with hub 18 and a plurality of airfoils 20 extending radially from hub 18. Each airfoil 20 includes tip 22, leading edge 24 and trailing edge (not shown).
  • In the embodiment shown, hub 18, airfoils 20 and shroud 12 are formed as an integral unit. They can be formed, for example, of a metallic material, for example, aluminum or titanium (including alloys) and machined into shape desired. In alternate embodiments, shroud 12 can be formed separately and connected to integrally bladed rotor fan 10.
  • Shroud 12 connects to tips 22 of airfoils 20, extending from leading edge 24 to trailing edge, and rotates with airfoils 20. Shroud 12 is spaced apart from case 14 with a tight clearance, for example, 0 mm (0 inches) to 2.54 mm (0.100 inches). Fan 10 acts to pull air into engine as airfoils 20 and shroud 12 spin in case 14.
  • As can be seen in FIGS. 1A-1B, integrally bladed rotor fan 10 is mounted to aircraft body 16. At this position, the boundary layer of air coming into the fan can have distortions, which can lead to vibrations or flutter in airfoils 20. As too much flutter in airfoils 20 could result in damage and/or a catastrophic failure of the airfoil 20, the minimization of flutter is desirable.
  • Shroud 12 connects to tips 22 of airfoils 20 to stabilize airfoils by providing a second connection to airfoils 20; the first connection being to hub 18 at the inner diameter and the second connection to shroud 12, at outer diameter. These stabilizing connections reduce the airfoil vibratory effects of fan 10, even when receiving a turbulent airflow. In past systems, blade flutter due to this turbulent airflow was controlled by using a variable area fan nozzle (“VAFN”) downstream from the fan. The VAFN was able to reduce flow through the fan by controlling the area at the back end of the fan, and thus increasing or decreasing back pressure. Although this was an effective way of reducing blade flutter, the VAFN is a large and heavy system which reduced efficiency of the overall engine.
  • Fan 10 with integral shroud 12 controls vibration and flutter in airfoils 20 without the need for a VAFN, reducing size and weight as compared to past systems. By forming shroud 12 integral to the fan 10, shroud 12 can also help to eliminate some stresses in airfoils 20 as it can carry some of blade load when fan 10 is in operation. Integrally formed shroud 12 will also eliminate blade tip 22 leakage in fan 10 (which can lead to loss of efficiency and potential stalls), and the tight clearance between shroud 12 and casing 14 will minimize performance losses caused by air going outside of the shroud 12.
  • FIG. 2A is a perspective view of a second embodiment of fan 10 with hybrid shroud 32, with part of fan casing 14 cut away, and FIG. 2B is a cross-sectional view of shroud 32. A partial portion of an aircraft body 16 is also shown. Fan 10 is an integrally bladed rotor type fan, with hub 18 and a plurality of airfoils 20 extending radially from hub 18. Each airfoil 20 has tip 22, leading edge 24 and trailing edge 25. Shroud 32 includes metallic portion 34 (with circumferentially curved portion 36, first ridge 38 and second ridge 40) and composite portion 42.
  • Shroud 32 metallic portion 34 connects to tips 22 of airfoils 20, and can be formed integral to fan 10 or can be formed separate and attached to tips 22. Circumferentially curved portion 36 of shroud connects to tips 22 and extends from leading edge 24 to trailing edge 25 of airfoils 20. First flange 38 extends perpendicular from circumferentially curved portion 36 outward, away from airfoils 20 at leading edge 24. Second flange 40 extends perpendicular from circumferentially curved portion 36 outward, away from airfoils 20 at trailing edge 25. Composite portion 42 can be a composite wrap that wraps circumferentially around circumferentially curved portion 36 between first flange 38 and second flange 40.
  • As in FIGS. 1A-1B, shroud 32 spins with fan 10 as fan pulls air into engine within case 14. Hybrid shroud 32 with metallic portion 34 and composite portion 42 allows for a high-strength, light-weight shroud 32 that can help stabilize airfoils 20 at outer diameter (tip 22) to reduce blade vibrations and flutter even when fan 10 is ingesting a very turbulent airflow. Metallic portion 34 of shroud 32 can be formed integral to fan 10 airfoils 20, ensuring high strength in connection at tips 22, and composite portion 42 can be wrapped around to reinforce metallic portion 34 without adding a lot of additional weight. Shroud 32 can also increase hoop strength of fan 10.
  • In summary, fan 10 with integral shroud 12, 32 reduces or eliminates vibrations or flutter in blades, eliminating the need for heavy and large VAFNs used in past systems to reduce flutter. Integral shroud 12, 32 connects to airfoil tips 22 to stabilize blade at outer diameter, thereby allowing fan 10 airfoils 20 to resist vibrations even when ingesting very turbulent airflows.
  • An integrally bladed rotor for use in a gas turbine engine includes a central hub; a plurality of airfoils extending from the central hub, each airfoil with a tip, a leading edge and a trailing edge; and a shroud with a metallic portion connecting to the tip of each airfoil to rotate with the airfoils.
  • Additional and/or alternative embodiments include the shroud being integral to the airfoils; the shroud being the same material as the airfoils; the entire shroud being metallic; the shroud comprising a metallic portion and a composite portion; the metallic portion comprising a metallic portion curved in the circumferential direction extending from the leading edge to the trailing edge of each airfoil, a first radial outward flange extending from the metallic portion at the leading edge, and a second radial outward flange extending from the metallic portion at the trailing edge; the composite portion wrapping around the metallic portion between the first radial outward flange and the second radial outward flange; a fan casing surrounding the integrally bladed rotor; the fan casing being spaced apart from the shroud with a tight clearance; the integrally bladed rotor being metallic; and/or the integrally bladed rotor being composite.
  • A fan includes an integrally bladed rotor with a plurality of blades with tips; a shroud extending around the blades and securing to the tips of each blade; and a fan casing surrounding the shroud, wherein the shroud is at least partially metallic.
  • Additional and/or alternative embodiments include the integrally bladed rotor and the shroud being entirely metallic; the integrally bladed rotor and the shroud being the same material; the integrally bladed rotor and the shroud being formed integrally; the shroud comprising a metallic portion and a composite portion; the metallic portion comprising a ring having an inner surface connected to the tips of the blades and an outer surface that includes a circumferential channel; the composite portion wrapping around the metallic portion in the circumferential channel; and/or the fan casing being spaced apart from the shroud with a tight clearance.
  • While the invention has been described with reference to an exemplary embodiment(s), it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the scope of the invention. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the invention without departing from the essential scope thereof. Therefore, it is intended that the invention not be limited to the particular embodiment(s) disclosed, but that the invention will include all embodiments falling within the scope of the appended claims.

Claims (19)

1. An integrally bladed rotor for use in a gas turbine engine comprising:
a central hub;
a plurality of airfoils extending from the central hub, each airfoil with a tip, a leading edge and a trailing edge; and
a shroud with a metallic portion connecting to the tip of each airfoil to rotate with the airfoils.
2. The integrally bladed rotor of claim 1, wherein the shroud is integral to the airfoils.
3. The integrally bladed rotor of claim 1, wherein the shroud is the same material as the airfoils.
4. The integrally bladed rotor of claim 1, wherein the entire shroud is metallic.
5. The integrally bladed rotor of claim 1, wherein the shroud comprises:
a metallic portion; and
a composite portion.
6. The integrally bladed rotor of claim 5, wherein the metallic portion comprises:
a metallic portion curved in the circumferential direction extending from the leading edge to the trailing edge of each airfoil;
a first radial outward flange extending from the metallic portion at the leading edge; and
a second radial outward flange extending from the metallic portion at the trailing edge.
7. The integrally bladed rotor of claim 6, wherein the composite portion wraps around the metallic portion between the first radial outward flange and the second radial outward flange.
8. The integrally bladed rotor of claim 1, and further comprising:
a fan casing surrounding the integrally bladed rotor.
9. The integrally bladed rotor of claim 8, wherein the fan casing is spaced apart from the shroud with a tight clearance.
10. The integrally bladed rotor of claim 1, wherein the integrally bladed rotor is metallic.
11. The integrally bladed rotor of claim 1, wherein the integrally bladed rotor is composite.
12. A fan comprising:
an integrally bladed rotor with a plurality of blades with tips;
a shroud extending around the blades and securing to the tips of each blade; and
a fan casing surrounding the shroud, wherein the shroud is at least partially metallic.
13. The fan of claim 12, wherein the integrally bladed rotor and the shroud are entirely metallic.
14. The fan of claim 12, wherein the integrally bladed rotor and the shroud are the same material.
15. The fan of claim 12, wherein the integrally bladed rotor and the shroud are formed integrally.
16. The fan of claim 12, wherein the shroud comprises:
a metallic portion; and
a composite portion.
17. The fan of claim 16, wherein the metallic portion comprises:
a ring having an inner surface connected to the tips of the blades and an outer surface that includes a circumferential channel.
18. The fan of claim 17, wherein the composite portion wraps around the metallic portion in the circumferential channel.
19. The fan of claim 12, wherein the fan casing is spaced apart from the shroud with a tight clearance.
US13/716,959 2012-12-17 2012-12-17 Fan with integral shroud Abandoned US20140169972A1 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
US13/716,959 US20140169972A1 (en) 2012-12-17 2012-12-17 Fan with integral shroud
PCT/US2013/072993 WO2014099365A1 (en) 2012-12-17 2013-12-04 Fan with integral shroud
EP13863829.1A EP2932039A4 (en) 2012-12-17 2013-12-04 Fan with integral shroud

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/716,959 US20140169972A1 (en) 2012-12-17 2012-12-17 Fan with integral shroud

Publications (1)

Publication Number Publication Date
US20140169972A1 true US20140169972A1 (en) 2014-06-19

Family

ID=50931097

Family Applications (1)

Application Number Title Priority Date Filing Date
US13/716,959 Abandoned US20140169972A1 (en) 2012-12-17 2012-12-17 Fan with integral shroud

Country Status (3)

Country Link
US (1) US20140169972A1 (en)
EP (1) EP2932039A4 (en)
WO (1) WO2014099365A1 (en)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140212261A1 (en) * 2012-12-19 2014-07-31 United Technologies Corporation Lightweight shrouded fan
FR3025562A1 (en) * 2014-09-04 2016-03-11 Snecma MONOBLOC AUBING DISC FOR A TURBOMACHINE
FR3027353A1 (en) * 2014-10-15 2016-04-22 Snecma TURBOMACHINE WHEEL
EP3378780A1 (en) * 2017-03-24 2018-09-26 Rolls-Royce plc Gas turbine engine
US20180347465A1 (en) * 2017-05-30 2018-12-06 United Technologies Corporation Systems for reducing deflection of a shroud that retains fan exit stators
EP3483393A1 (en) * 2017-11-14 2019-05-15 United Technologies Corporation Fan assembly of a gas turbine engine with a tip shroud
US10421553B2 (en) 2015-01-20 2019-09-24 United Technologies Corporation Pusher fan engine with in wing configuration
US10626884B2 (en) * 2016-12-09 2020-04-21 Hamilton Sundstrand Corporation Systems and methods for making airfoils
US20250084854A1 (en) * 2023-09-13 2025-03-13 Honda Motor Co., Ltd. Fan assembly

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3314651A (en) * 1964-04-09 1967-04-18 Rolls Royce Sealing device
US3556675A (en) * 1969-01-29 1971-01-19 Gen Electric Turbomachinery rotor with integral shroud
US5221187A (en) * 1990-12-21 1993-06-22 Flatgeotechtechnologie Per La Terra S.P.A. Axial fan, particularly for motor vehicles for agricultural use

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2952442A (en) * 1957-05-28 1960-09-13 Studebaker Packard Corp Rotating shroud
US4464094A (en) * 1979-05-04 1984-08-07 Trw Inc. Turbine engine component and method of making the same
US5201850A (en) * 1991-02-15 1993-04-13 General Electric Company Rotor tip shroud damper including damper wires
US5522705A (en) * 1994-05-13 1996-06-04 United Technologies Corporation Friction damper for gas turbine engine blades
US6223524B1 (en) * 1998-01-23 2001-05-01 Diversitech, Inc. Shrouds for gas turbine engines and methods for making the same
US6454535B1 (en) * 2000-10-31 2002-09-24 General Electric Company Blisk
US6881036B2 (en) * 2002-09-03 2005-04-19 United Technologies Corporation Composite integrally bladed rotor
EP2031187B1 (en) * 2004-12-08 2012-07-18 Volvo Aero Corporation A wheel for a rotating flow machine
FR2903921B1 (en) * 2006-07-19 2009-06-05 Snecma Sa METHOD FOR MANUFACTURING A MONOBLOCK AND MOLDING BLADE DISK FOR CARRYING OUT THE METHOD
US8206086B1 (en) * 2008-04-22 2012-06-26 Florida Turbine Technologies, Inc. Turbofan hybrid metallic and plastic inlet case
DE102010021220A1 (en) * 2010-05-21 2011-11-24 Mtu Aero Engines Gmbh Rotor for turbine engine, has rotor base body and blades arranged on periphery of rotor base body, where cable is provided for receiving centrifugal force
WO2012091821A1 (en) * 2010-12-30 2012-07-05 General Electric Company Apparatus and method for measuring runout
US8105039B1 (en) * 2011-04-01 2012-01-31 United Technologies Corp. Airfoil tip shroud damper
CN102418562B (en) * 2011-08-15 2014-04-02 清华大学 Fiber winding prestress turbine rotor

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3314651A (en) * 1964-04-09 1967-04-18 Rolls Royce Sealing device
US3556675A (en) * 1969-01-29 1971-01-19 Gen Electric Turbomachinery rotor with integral shroud
US5221187A (en) * 1990-12-21 1993-06-22 Flatgeotechtechnologie Per La Terra S.P.A. Axial fan, particularly for motor vehicles for agricultural use

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140212261A1 (en) * 2012-12-19 2014-07-31 United Technologies Corporation Lightweight shrouded fan
FR3025562A1 (en) * 2014-09-04 2016-03-11 Snecma MONOBLOC AUBING DISC FOR A TURBOMACHINE
FR3027353A1 (en) * 2014-10-15 2016-04-22 Snecma TURBOMACHINE WHEEL
US10421553B2 (en) 2015-01-20 2019-09-24 United Technologies Corporation Pusher fan engine with in wing configuration
US10626884B2 (en) * 2016-12-09 2020-04-21 Hamilton Sundstrand Corporation Systems and methods for making airfoils
EP3378780A1 (en) * 2017-03-24 2018-09-26 Rolls-Royce plc Gas turbine engine
US10711614B2 (en) 2017-03-24 2020-07-14 Rolls-Royce Plc Gas turbine engine
US20180347465A1 (en) * 2017-05-30 2018-12-06 United Technologies Corporation Systems for reducing deflection of a shroud that retains fan exit stators
US10557412B2 (en) * 2017-05-30 2020-02-11 United Technologies Corporation Systems for reducing deflection of a shroud that retains fan exit stators
EP3483393A1 (en) * 2017-11-14 2019-05-15 United Technologies Corporation Fan assembly of a gas turbine engine with a tip shroud
US10724535B2 (en) 2017-11-14 2020-07-28 Raytheon Technologies Corporation Fan assembly of a gas turbine engine with a tip shroud
US20250084854A1 (en) * 2023-09-13 2025-03-13 Honda Motor Co., Ltd. Fan assembly

Also Published As

Publication number Publication date
EP2932039A1 (en) 2015-10-21
EP2932039A4 (en) 2015-12-23
WO2014099365A1 (en) 2014-06-26

Similar Documents

Publication Publication Date Title
US20140169972A1 (en) Fan with integral shroud
US11300136B2 (en) Aircraft fan with low part-span solidity
CN103459774B (en) There is the compressor airfoil at the tip upper counterangle
US9630704B2 (en) Blade for a fan of a turbomachine, notably of the unducted fan type, corresponding fan and corresponding turbomachine
US8221081B2 (en) Turbomachine having an unducted fan provided with air guide means
US9334878B2 (en) Vortex generators for generating vortices upstream of a cascade of compressor blades
US11933193B2 (en) Turbine engine with an airfoil having a set of dimples
EP2333251A2 (en) Fan containment case
US9650916B2 (en) Turbomachine cooling systems
JP2008163950A (en) Guide vane and method of fabricating the same
US11118466B2 (en) Compressor stator with leading edge fillet
CA2833986A1 (en) Low hub-to-tip ratio fan for a turbofan gas turbine engine
US10408227B2 (en) Airfoil with stress-reducing fillet adapted for use in a gas turbine engine
EP2896794B1 (en) Blisk
US9222437B2 (en) Transition duct for use in a turbine engine and method of assembly
US20190368361A1 (en) Non-symmetric fan blade tip cladding
US11274563B2 (en) Turbine rear frame for a turbine engine
US9863252B2 (en) Single-piece blisk for turbomachine fan comprising an upstream and/or downstream recess making its blades more flexible
US20170074101A1 (en) Axial turbo machine
JP6167677B2 (en) Wings and fans in fans
US20060198726A1 (en) Apparatus for eliminating compressor stator vibration induced by tip leakage vortex bursting
US10465555B2 (en) Airfoil for axial flow machine
EP3770379B1 (en) Compressor stator
JP5647426B2 (en) Method and apparatus for structural exit guide vanes
US20160102580A1 (en) Power turbine inlet duct lip

Legal Events

Date Code Title Description
AS Assignment

Owner name: UNITED TECHNOLOGIES CORPORATION, CONNECTICUT

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:SUCIU, GABRIEL L.;CHANDLER, JESSE M.;MERRY, BRIAN D.;REEL/FRAME:029482/0829

Effective date: 20121214

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION