Granted Patent B2

US 12,655,773 · App. 18/789,153 · Granted Jun 16, 2026

Inventors: Nitesh Jain (Bengaluru, IN); Nicholas J. Kray (Evendale, OH); Veeraraju V (Bengaluru, IN); Deepak Ghiya (Bengaluru, IN); Sreekanth Kumar Dorbala (Bengaluru, IN); Kishore Budumuru (Bengaluru, IN); Apostolos Karafillis (Lynn, MA); Thomas Chadwick Waldman (Lynn, MA); Theodore E. Anderson (West Chester, OH); Joel F. Kirk (Evendale, OH); Edward A. Rainous (West Chester, OH); Michael E. Eriksen (West Chester, OH); Mojibur Rahman (Evendale, OH)

Assignee: General Electric Company

F01D21/045F01D25/24F05D2220/36F05D2240/20

Abstract

Claims (24)

1 . A casing apparatus for an aircraft engine, the casing apparatus comprising:

a containment casing including a ridge on an exterior surface of the containment casing; and

a deflector plate including a first end and a second end, the first end directly coupled to the ridge, the second end uncoupled to the containment casing, wherein the first end of the deflector plate is formed of a first material, and the ridge is formed of a second material different than the first material.

2 . The casing apparatus of claim 1 , wherein the containment casing is a soft wall containment casing.

3 . The casing apparatus of claim 2 , wherein the first material has a higher density than the second material.

4 . The casing apparatus of claim 1 , wherein the deflector plate is aligned with one or more components associated with the aircraft engine and positioned outside of the containment casing to deflect fan blade fragments away from the one or more components.

5 . The casing apparatus of claim 1 , wherein the deflector plate is positioned against the containment casing between the first end and the second end.

6 . The casing apparatus of claim 1 , wherein the first end of the deflector plate is positioned further than the second end of the deflector plate from an axial centerline axis of the aircraft engine in a radial direction defined by the aircraft engine.

7 . The casing apparatus of claim 1 , further including a lattice structure or a honeycomb structure positioned on a portion of the deflector plate opposite the containment casing.

8 . The casing apparatus of claim 7 , wherein a first portion of the lattice structure or the honeycomb structure is positioned on the portion of the deflector plate, and wherein a second portion of the lattice structure or the honeycomb structure is in contact with the exterior surface of the containment casing.

9 . The casing apparatus of claim 7 , further including a cover layer positioned around the lattice structure or the honeycomb structure.

10 . The casing apparatus of claim 9 , wherein the cover layer includes a metal sheet or a composite sheet.

11 . The casing apparatus of claim 9 , further including a wrap layer positioned around the cover layer, the wrap layer including a different material than the cover layer.

12 . A casing apparatus for an aircraft engine, the casing apparatus comprising:

a containment casing including a ridge on an exterior surface of the containment casing; and

a deflector plate including a first end and a second end, the first end coupled to the ridge, the second end uncoupled to the containment casing, wherein a span of the deflector plate extends from the first end to the second end in an axial direction defined by the aircraft engine, and wherein a portion of the containment casing is aligned with the deflector plate throughout the span, wherein the portion of the containment casing is radially inward of the deflector plate throughout the span.

13 . The casing apparatus of claim 12 , wherein the containment casing includes a first set of metal bands and a second set of metal bands traversing the first set of metal bands, the first set of metal bands and the second set of metal bands are disposed along a circumference of the containment casing to surround at least a portion of the aircraft engine.

14 . The casing apparatus of claim 13 , wherein the first set of metal bands and the second set of metal bands include aluminum-lithium.

15 . The casing apparatus of claim 13 , further including at least a third set of metal bands traversing or surrounding the first set of metal bands and the second set of metal bands.

16 . The casing apparatus of claim 13 , further including a lattice structure or a honeycomb structure positioned on an exterior surface of the deflector plate at the second end.

17 . The casing apparatus of claim 16 , further including at least one of a cover layer or a wrap layer positioned around the lattice structure or the honeycomb structure and coupled to the containment casing.

18 . A casing apparatus for an aircraft engine, the casing apparatus comprising:

a containment casing including a ridge on an exterior surface of the containment casing; and

a deflector plate including a first end and a second end, the first end coupled to the ridge, the second end uncoupled to the containment casing, wherein the deflector plate is aligned with one or more components associated with the aircraft engine in an axial direction, and wherein the deflector plate is positioned radially outward of the containment casing to deflect fan blade fragments away from the one or more components, wherein the first end of the deflector plate is formed of a first material, and the ridge is formed of a second material different than the first material, and wherein the first material has a higher density than the second material.

Assignments (1)

Continuity (2)

References Cited (54)