Gas turbine engine

Patent metadata

Field	Value
Publication number	US-10865649-B2
Application number	US-201715467328-A
Country	US
Kind code	B2
Filing date	Mar 23, 2017
Priority date	Apr 20, 2016
Publication date	Dec 15, 2020
Grant date	Dec 15, 2020

Abstract

A gas turbine engine that includes a fan blade having a tip, a root, a pressure side, a suction side, a trailing edge and a leading edge, the fan blade including a laminate body defined by a plurality of plies comprising reinforcement fibres, wherein an angle of the fibres in the plies from the trailing edge to the leading edge at the suction side and/or the pressure side of the blade are arranged such that the laminate body is unbalanced so that, during rotation of the fan blade, the fan blade deforms such that a centre of mass of the blade rotates about a centre of rotation of the fan so as to move the centre of mass towards a balanced position.

First claim

The invention claimed is:

1. A gas turbine engine comprising
a fan blade having a tip, a root, a pressure side, a suction side, a trailing edge and a leading edge, the fan blade comprising:
a laminate body defined by a plurality of plies comprising reinforcement fibres, wherein:
an angle of the fibres in the plies from the trailing edge to the leading edge at the suction side and the pressure side of the fan blade are arranged such that the laminate body is unbalanced from the trailing edge to the leading edge so that, during rotation of the fan blade, the fan blade deforms such that a centre of mass of the fan blade rotates about a centre of rotation of the fan blade so as to move the centre of mass towards a balanced position,
the fan blade comprises an inner region defined by a plurality of plies between the plies at the suction side and at the pressure side, and
when at a state of rest, the angle of the fibres of the plies at the pressure side and the suction side continuously varies from the root to the tip of the fan blade and the plurality of plies of the inner region are arranged to be balanced and symmetric and a direction of the fibres of the plies of the inner region is substantially 0 degrees relative to a radial axis of the fan blade from the root to the tip of the fan blade.

2. The gas turbine engine according to claim 1 , wherein the fibres in the plies at the pressure side and/or the suction side are arranged so as to define a non-symmetric laminate.

3. The gas turbine engine according to claim 2 , wherein the fibres in the plies at the pressure side and/or the suction side are arranged to be anti-symmetric.

4. The gas turbine engine according to claim 1 , wherein the plies at the pressure side and/or the suction side are arranged such that the fan blade is symmetric in a region proximal to the root and non-symmetric in a region proximal to the tip.

5. The gas turbine engine according to claim 1 , wherein a fibre direction of the plies on the pressure side and/or the suction side of the fan blade have a positive or a negative angle in a region near the root of the fan blade.

6. The gas turbine engine according to claim 1 , wherein a fibre direction of the plies at the suction side has a negative angle and/or a fibre direction of the plies on the pressure side of the fan blade has a positive angle proximal to the tip of the fan blade.

7. The gas turbine engine according to claim 1 , wherein the inner region has a thickness between 30% and 70% of an overall blade thickness.

8. A method of manufacturing a fan blade of the gas turbine engine according to claim 1 , the method comprising laying up a plurality of plies so as to define a laminate, and varying the fibre direction within the laminate such that the laminate is unbalanced.

9. The method according to claim 8 , comprising defining the plies and the fibre direction of the plies using a pre-preg tape.

10. The method according to claim 9 , wherein the plies are laid up using automated fibre placement.

11. A gas turbine engine comprising
a fan blade comprising a tip, a root, a pressure side, a suction side, a trailing edge and a leading edge, the fan blade comprising:
a laminate body defined by a plurality of plies comprising reinforcement fibres, wherein:
an angle of the fibres in the plies from the trailing edge to the leading edge at the pressure side and the suction side are arranged such that the laminate body is non-symmetric from the trailing edge to the leading edge,
the fan blade comprises an inner region defined by a plurality of plies between the plies at the suction side and at the pressure side, and
when at a state of rest, a direction of the reinforcement fibres in the plies at the pressure side and the suction side continuously varies from the root to the tip of the fan blade and the plurality of plies of the inner region are arranged to be balanced and symmetric and a direction of the fibres of the plies of the inner region is substantially 0 degrees relative to a radial axis of the fan blade from the root to the tip of the fan blade.

12. A method of manufacturing a composite fan blade for a gas turbine engine, the composite fan blade including a laminate having a plurality of stacked plies, and the fan blade including a tip, a root, a pressure side, a suction side, a trailing edge and a leading edge, the method comprising:
designing the plies of the laminate such that the laminate is unbalanced from the trailing edge to the leading edge so as to promote deformation of the fan blade when used under take off conditions compared to when used under cruise conditions,
wherein, when at a state of rest, an angle of fibres of the plies at the pressure side and the suction side continuously varies from the root to the tip of the fan blade and a plurality of plies of an inner region between the plies at the suction side and at the pressure side are arranged to be balanced and symmetric and a direction of the fibres of the plies of the inner region is substantially 0 degrees relative to a radial axis of the fan blade from the root to the tip of the fan blade.

13. The method according to claim 12 , comprising designing the plies of the laminate such that the laminate is non-symmetric, and selecting the angle of the fibres of the plies and the extent of non-symmetry to achieve a first configuration of fan blade under take off conditions and a second configuration of the fan blade under cruise conditions.

14. The method according to claim 13 , wherein the angle of the fibres and the extent of non-symmetry of the plies is selected so as to utilise change in temperature between take off and cruise, and/or the difference in forces acting on the fan blade.

Assignees

• Rolls Royce Plc

Inventors

• Thomas Matthew

Classifications

• F01D5/282 Primary

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

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F04D29/325

  for axial flow fans (blade mountings F04D29/34, blades F04D29/38) · CPC title

• F04D29/324

  Blades · CPC title

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title