Composite disk

Patent metadata

Field	Value
Publication number	US-9976429-B2
Application number	US-201514734091-A
Country	US
Kind code	B2
Filing date	Jun 9, 2015
Priority date	Jun 9, 2015
Publication date	May 22, 2018
Grant date	May 22, 2018

Abstract

A gas turbine engine composite disk includes dovetail slots between disk posts extending radially inwardly from a periphery, a hub ring of composite plies circumscribed about a centerline axis, and radial plies extending radially away from hub ring into disk posts. A segmented intermediate ring concentric with and located radially outwardly of hub ring includes intermediate ring segments having nested plies with annular bases circumscribed about centerline axis and substantially radially extending clockwise and counter-clockwise radial ply arms. An outer segmented ring may be concentric with and located radially outwardly of intermediate ring, include annular outer ring segments with circumferentially stacked composite plies disposed within intermediate ring segments between clockwise and counter-clockwise radial ply arms and radially outwardly of annular bases. An outer skin of outermost composite covering plies may extend circumferentially around composite disk. Circumferential and radial composite plies may include circumferentially and radially oriented fibers.

First claim

What is claimed is:

1. A gas turbine engine composite disk comprising:
dovetail slots between disk posts extending radially inwardly from a radially outer periphery of the composite disk;
a hub ring of composite plies circumscribed about a centerline axis;
radial plies extending radially away from the hub ring and into the disk posts; and
a segmented intermediate ring concentric with and located radially outwardly of the hub ring;
further comprising an outer skin including one or more outermost composite covering plies extending circumferentially around the composite disk, covering the disk posts, and bounding the dovetail slots therebetween.

2. The composite disk as claimed in claim 1 ,
further comprising the composite plies wrapped in a spiral or the composite plies being concentric, annular, and circular in cross-section.

3. A gas turbine engine composite disk comprising:
dovetail slots between disk posts extending radially inwardly from a radially outer periphery of the composite disk;
a hub ring of composite plies circumscribed about a centerline axis;
radial plies extending radially away from the hub ring and into the disk posts; and
a segmented intermediate ring concentric with and located radially outwardly of the hub ring;
wherein the segmented intermediate ring comprises annular intermediate ring segments,
each of the intermediate ring segments including nested plies, and
each of the nested plies including an annular base circumscribed about the centerline axis and substantially radially extending clockwise and counter-clockwise radial ply arms at clockwise and counter-clockwise ends of the annular base wherein the radial plies include the clockwise and counter-clockwise radial ply arms.

4. The composite disk as claimed in claim 3 , further comprising the composite plies wrapped in a spiral or the composite plies being concentric, annular, and circular in cross-section.

5. The composite disk as claimed in claim 3 , further comprising an outer skin including one or more outermost composite covering plies extending circumferentially around the composite disk, covering the disk posts, and bounding the dovetail slots therebetween and the outer skin covering radial outer edges of the clockwise and counter-clockwise radial ply arms.

6. The composite disk as claimed in claim 5 , further comprising:
circumferential composite plies in the hub ring, the annular base, and the outer skin covering post tops of the disk posts and bottoms of the dovetail slots;
the circumferential composite plies including circumferentially oriented fibers;
radial composite plies in the clockwise and counter-clockwise radial ply arms and the outer skin along radially extending post sides of the disk posts bounding the dovetail slots; and
the radial composite plies including radially oriented fibers.

7. The composite disk as claimed in claim 3 , further comprising:
an outer segmented ring concentric with and located radially outwardly of the segmented intermediate ring,
the outer segmented ring including annular outer ring segments, and
each of the outer ring segments including circumferentially stacked composite plies disposed within each of the intermediate ring segments between the substantially radially extending clockwise and counter-clockwise radial ply arms and radially outwardly of the annular bases.

8. The composite disk as claimed in claim 7 , further comprising:
an outer skin including one or more outermost composite covering plies extending circumferentially around the composite disk;
the outer skin covering the outer ring segments and the disk posts and bounding the dovetail slots therebetween; and
the outer skin covering radial outer edges of the clockwise and counter-clockwise radial ply arms.

9. The composite disk as claimed in claim 8 , further comprising:
circumferential composite plies in the hub ring, the annular base, and the outer skin covering post tops of the disk posts and bottoms of the dovetail slots;
the circumferential composite plies including circumferentially oriented fibers;
radial composite plies in the clockwise and counter-clockwise radial ply arms and the outer skin along radially extending post sides of the disk posts bounding the dovetail slots; and
the radial composite plies including radially oriented fibers.

10. The composite disk as claimed in claim 9 , further comprising the dovetail slots flaring out towards the bottoms.

11. A gas turbine engine composite disk and blade assembly comprising:
a composite disk including dovetail slots between disk posts extending radially inwardly from a radially outer periphery of the composite disk,
the dovetail slots including bottoms between disk posts,
blades having airfoils attached to outwardly flared dovetail roots,
the dovetail roots disposed in the dovetail slots,
the dovetail roots retained in the mating flared out dovetail slots,
a hub ring of composite plies circumscribed about a centerline axis, and
radial plies extending radially away from the hub ring and into the disk posts.

12. The assembly as claimed in claim 11 , further comprising the composite plies wrapped in a spiral or the composite plies being concentric, annular, and circular in cross-section.

13. The assembly as claimed in claim 11 , further comprising an outer skin including one or more outermost composite covering plies extending circumferentially around the composite disk, covering the disk posts, and bounding the dovetail slots therebetween.

14. The assembly as claimed in claim 11 , further comprising:
a segmented intermediate ring concentric with and located radially outwardly of the hub ring,
the intermediate ring including annular intermediate ring segments,
each of the intermediate ring segments including nested plies, and
each of the nested plies including an annular base circumscribed about the centerline axis and substantially radially extending clockwise and counter-clockwise radial ply arms at clockwise and counter-clockwise ends of the annular base wherein the radial plies include the clockwise and counter-clockwise radial ply arms.

15. The assembly as claimed in claim 14 , further comprising an outer skin including one or more outermost composite covering plies extending circumferentially around the composite disk, covering the disk posts, and bounding the dovetail slots therebetween and the outer skin covering radial outer edges of the clockwise and counter-clockwise radial ply arms.

16. The assembly as claimed in claim 15 , further comprising:
circumferential composite plies in the hub ring, the annular base, and the outer skin covering post tops of the disk posts and the bottoms of the dovetail slots;
the circumferential composite plies including circumferentially oriented fibers;
radial composite plies in the clockwise and counter-clockwise radial ply arms and the outer skin along radially extending post sides of the disk posts bounding the dovetail slots; and
the radial composite plies including radially oriented fibers.

17. The assembly as claimed in claim 14 , further comprising:
an outer segmented ring concentric with and located radially outwardly of the segmented intermediate ring,
the outer segmented ring including annular outer ring segments, and
each of the outer ring segments including circumferentially stacked composite plies disposed within each of the intermediate ring segments between the substantially radially extending clockwise and counter-clockwise radial ply arms and radially outwardly of the annular bases.

18. The assemb

Assignees

• Gen Electric

Inventors

• Kray Nicholas Joseph
• Bhuvaraghan Baskaran
• Jain Nitesh

Classifications

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title

• F01D5/3007

  of axial insertion type · CPC title

• B29C70/48

  and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM] {, e.g. by vacuum} · CPC title

• F01D5/282

  Selecting composite materials, e.g. blades with reinforcing filaments · CPC title

• F01D5/028 Primary

  the rotor disc being formed of sheet laminae (rotor blade aggregates of unitary construction F01D5/34) · CPC title