Spinner for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10100644-B2
Application number	US-201514635412-A
Country	US
Kind code	B2
Filing date	Mar 2, 2015
Priority date	Mar 3, 2014
Publication date	Oct 16, 2018
Grant date	Oct 16, 2018

Abstract

A spinner for use in a gas turbine engine includes a body and an aft ring coupled to the body. The body is symmetrically formed by filament winding around a central axis. The aft ring includes a band coupled to the body and a plurality of fairings that extend outward in a radial direction from the band away from the central axis.

First claim

What is claimed is:

1. A spinner for use in a gas turbine engine comprising
a unitary filament-wound body formed substantially symmetrically around a central axis, the body including a side wall that forms a majority of an exterior radially-outwardly facing surface of the spinner and that has a diameter that increases along the central axis from a forward side of the body to an aft side of the body, and
an aft ring including a band that overlaps a radially-outwardly facing portion of the side wall along the aft side of the body and a plurality of fairings that extend outward in a radial direction from the band away from the central axis,
wherein the aft ring includes a plurality of segments each arranged to extend around a portion of the diameter of the aft ring,
wherein each segment includes a plurality of layers in which at least one radially-outer layer extends further in the axial direction along the body toward the forward side of the body than at least one radially-inner layer.

2. The spinner of claim 1 , wherein the aft ring is formed from a composite material and is bonded to the body by a resin.

3. The spinner of claim 1 , wherein each segment is formed to include a first fairing and a second fairing.

4. The spinner of claim 1 , wherein each segment is formed to include only one fairing.

5. The spinner of claim 1 , wherein each segment is spaced circumferentially apart from adjacent segments to form abutment joints between each pair of adjacent segments.

6. A spinner for use in a gas turbine engine comprising
a unitary filament-wound body formed substantially symmetrically around a central axis, the body including a side wall that forms a majority of an exterior radially-outwardly facing surface of the spinner and that has a diameter that increases along the central axis from a forward side of the body to an aft side of the body, and
an aft ring including a band that overlaps a radially-outwardly facing portion of the side wall along the aft side of the body and a plurality of fairings that extend outward in a radial direction from the band away from the central axis,
wherein the aft ring includes a plurality of segments each arranged to extend around a portion of the diameter of the aft ring,
wherein each segment is arranged to circumferentially overlap a portion of one adjacent segment to form circumferentially overlapping joints between each pair of adjacent segments.

7. The spinner of claim 6 , wherein each segment includes a plurality of layers in which at least one radially-outer layer extends further in the axial direction along the body toward the forward side of the body than at least one radially-inner layer.

8. The spinner of claim 6 , wherein each segment includes a plurality of layers in which at least one radially-inner layer extends circumferentially under a radially-outer layer of an adjacent segment and abuts a radially-inner layer of the adjacent segment.

9. A spinner for use in a gas turbine engine comprising
a unitary body comprising composite materials, the body including a side wall that forms a majority of an exterior radially-outwardly facing surface of the spinner and that has a diameter that increases along a central axis from a forward side of the body to an aft side of the body, and
an asymmetric aft ring comprising composite materials that overlaps a radially-outwardly facing portion of the side wall along the aft side of the body, the aft ring including a first layer of woven-fabric plies and a second layer of woven-fabric plies arranged circumferentially around the first layer of woven-fabric plies, the first layer of woven-fabric plies arranged circumferentially adjacent to one another to form circumferential joints between plies, and the second layer of plies arranged circumferentially adjacent to one another to form circumferential joints between plies,
wherein the circumferential joints of the first layer of plies are circumferentially offset from the circumferential joints of the second layer of plies by at least one fairing that extends outward in a radial direction away from the central axis.

10. The spinner of claim 9 , wherein the second layer of plies is radially-adjacent to the first layer of plies so that the aft ring is free of plies sandwiched between the first layer of plies and the second layer of plies.

11. The spinner of claim 9 , wherein the at least one fairing is formed by a plug arranged radially between the side wall and the first layer of plies.

12. The spinner of claim 11 , wherein the plug is arranged radially between the side wall and the second layer of plies.

13. The spinner of claim 11 , wherein the plug includes reinforcing fibers suspended in a matrix material.

14. A fan assembly comprising
a bladed wheel including a hub and a plurality of fan blades coupled to the hub to extend radially outward from the hub, and
a spinner coupled to the hub, the spinner including a unitary filament-wound body having a side wall arranged around a central axis that forms a majority of an exterior radially-outwardly facing surface of the spinner and an aft ring made from composite materials bonded to the side wall of the body, the aft ring including a band that overlaps a radially-outwardly facing portion of the side wall adjacent to the hub and a plurality of fairings that extend outward in a radial direction from the band away from the central axis ahead of each fan blade included in the bladed wheel,
wherein the aft ring is formed from a plurality of segments each arranged to extend around a portion of the diameter of the aft ring,
wherein each segment is arranged to circumferentially overlap a portion of one adjacent segment to form circumferentially overlapping joints between each pair of adjacent segments.

Assignees

• Rolls Royce Corp

Inventors

• Romanowski Erin M
• Engebretsen Eric W
• Scott Matthew A

Classifications

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• Y02T50/673

  Cross-Sectional Technologies · mapped topic

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F02C7/04

  Air intakes for gas-turbine plants or jet-propulsion plants · CPC title

• F01D5/12 Primary

  Blades ({specially adapted for radial flow machines or engines F01D5/04}; blade roots F01D5/30; rotors with blades adjustable in operation F01D7/00; stator blades F01D9/02) · CPC title