Containment casing

Patent metadata

Field	Value
Publication number	US-10428681-B2
Application number	US-201615153339-A
Country	US
Kind code	B2
Filing date	May 12, 2016
Priority date	Jun 5, 2015
Publication date	Oct 1, 2019
Grant date	Oct 1, 2019

Abstract

The present invention provides a gas turbine engine comprising a tubular containment casing surrounding a rotary fan blade assembly. The radially outer perimeter (and optionally the radially inner perimeter) of the radial cross-sectional profile of the containment casing is non-circular e.g. polygonal, corrugated, fluted or wavy.

First claim

The invention claimed is:

1. A gas turbine engine, comprising:
a tubular containment casing comprising (i) a series of axially-extending wall portions each having a radially outer surface and a radially inner surface, (ii) a series of axially-extending external edges between the outer surfaces of adjoining ones of the wall portions, and (iii) a series of axially-extending internal joins between the inner surfaces of adjoining ones of the wall portions; and
a rotary fan blade assembly,
wherein a radially outer perimeter and a radially inner perimeter of a radial cross-sectional profile of a portion of the containment casing surrounding the fan blade assembly are polygonal.

2. The gas turbine engine according to claim 1 , wherein at least one of the radially outer perimeter and the radially inner perimeter is a square, pentagon, hexagon, heptagon, octagon, nonagon, decagon, hendecagon or dodecagon.

3. The gas turbine engine according to claim 1 , wherein the number of fan blades in the rotary fan blade assembly is not divisible by the number of axially-extending wall portions.

4. The gas turbine engine according to claim 1 , wherein at least one of the radially outer and inner surfaces of each axially-extending wall portion is substantially planar.

5. The gas turbine engine according to claim 1 , wherein:
the tubular containment casing comprises opposing axial end portions each having a circular cross-sectional profile; and
the axially-extending wall portions extend between the axial end portions of the containment casing.

6. The gas turbine engine according to claim 1 , wherein the axially-extending wall portions are formed of a fibre-reinforced organic matrix composite.

7. The gas turbine engine according to claim 1 , further comprising a radially outer layer of ballistic wrapping.

8. The gas turbine engine according to claim 1 , further comprising a radially inner liner for defining an annular fan blade path.

Assignees

• Rolls Royce Plc

Inventors

• Finlayson James A
• Evans Dale E
• Care Ian C D

Classifications

• F01D21/045 Primary

  special arrangements in stators or in rotors dealing with breaking-off of part of rotor · CPC title

• F05D2300/603

  Composites; e.g. fibre-reinforced · CPC title

• F05D2250/61

  corrugated · CPC title

• F01D25/24 Primary

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• F05D2250/184

  sinusoidal · CPC title