Web connected dual aerofoil members

Patent metadata

Field	Value
Publication number	US-9482095-B2
Application number	US-201313967700-A
Country	US
Kind code	B2
Filing date	Aug 15, 2013
Priority date	Sep 6, 2012
Publication date	Nov 1, 2016
Grant date	Nov 1, 2016

Abstract

A rotor blade assembly for a gas turbine engine includes two aerofoil members joined together at their roots by a blade assembly attachment web. The rotor blade assembly is made from a composite material, for example an organic fiber composite material. The blade assembly attachment web is used to attach a plurality of rotor blade assemblies to the rest of the gas turbine engine in order to form a rotor stage. The rotor stage may, for example, be the fan stage of a turbofan gas turbine engine.

First claim

I claim:

1. A rotor blade stage and a rotor blade assembly for a gas turbine engine, wherein the rotor blade assembly comprises:
two aerofoil members, each extending from a root to a tip; and
a blade assembly attachment web extending between the roots of the two aerofoil members and arranged for use in attaching the rotor blade assembly to the rest of the gas turbine engine in use, wherein:
the two aerofoil members and the blade assembly attachment web are integrally formed using a fiber-reinforced composite material; and
wherein the, rotor blade stage comprises:
a plurality of the rotor blade assemblies;
a rotatable hub portion onto which each of the plurality of rotor blade assemblies is fixed using the blade assembly attachment web of each of the plurality of rotor blade assemblies, wherein:
the rotatable hub portion comprises a plurality of mounting surfaces,
the plurality of mounting surfaces are separated from each other by dividing portions which project in a radially outward direction from the rotatable hub portion thereby dividing the blade assembly attachment web of each of the plurality of rotor blade assemblies, and
the blade assembly attachment web of each of the plurality of rotor blade assemblies having a radially inner surface that is shaped to cooperate with a respective one of the plurality of mounting surfaces so as to locate each of the plurality of rotor blade assemblies on the rotatable hub portion.

2. The rotor blade stage and the rotor blade assembly according to claim 1 , wherein the blade assembly attachment web has the radially inner surface and a radially outer surface with respect to a rotational axis of the gas turbine engine in use, the radially inner surface being shaped to cooperate with the plurality of mounting surfaces of the gas turbine engine to allow the plurality of rotor blade assemblies to be located in position in the gas turbine engine.

3. The rotor blade stage and the rotor blade assembly according to claim 1 , wherein the two aerofoil members are fan blades, wherein the gas turbine engine comprises a turbofan gas turbine engine, and the plurality of rotor blade assemblies are part of a fan stage of the turbofan gas turbine engine.

4. The rotor blade stage and the rotor blade assembly of the gas turbine engine according to claim 1 , wherein each mounting surface of the plurality of mounting surfaces is formed by a radially hub outer surface of a respective recess in the rotatable hub portion.

5. The rotor blade stage and the rotor blade assembly according to claim 1 , further comprising a plurality of attachment covers, each rotor blade assembly of the plurality of rotor blade assemblies having a corresponding attachment cover, wherein:
each blade assembly attachment web is fixed between its respective mounting surface and attachment cover.

6. The rotor blade stage and the rotor blade assembly according to claim 5 , wherein each of the plurality of attachment covers has a radially outer surface which, in use, is a gas-washed surface.

7. The rotor blade stage and the rotor blade assembly according to claim 1 , wherein the rotor blade stage is a fan stage of a turbofan gas turbine engine.

8. A gas turbine engine comprising the rotor blade stage and the rotor blade assembly according to claim 1 .

9. A method of assembling a rotor blade stage of a gas turbine engine comprising:
integrally forming a rotor blade assembly using fiber-reinforced composite material, wherein the rotor blade assembly comprises:
two aerofoil members, each extending from a root to a tip; and
a blade assembly attachment web extending between the roots of the two aerofoil members;

locating a plurality of rotor blade assemblies on a rotatable hub portion by a radially inner surface of the blade assembly attachment web that is shaped to cooperate with a respective one of a plurality of mounting surfaces on the rotatable hub portion, wherein
the plurality of mounting surfaces are separated from each other by dividing portions which project in a radially outward direction from the rotatable hub portion thereby dividing the blade assembly attachment web of each of the plurality of rotor blade assemblies; and

clamping the blade assembly attachment web of each of the plurality of rotor blade assemblies between the rotatable hub portion and a respective attachment cover.

10. The method of assembling the rotor blade stage of the gas turbine engine according to claim 9 , wherein the attachment cover has a radially outer surface which, in use, is a gas-washed surface.

Assignees

• Rolls Royce Plc

Inventors

• Drane Andrew James

Classifications

• F01D5/14 Primary

  Form or construction (selecting particular materials, measures against erosion or corrosion F01D5/28) · CPC title

• F05D2300/603

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

• F04D29/388

  characterised by construction · CPC title

• F04D29/023 Primary

  especially adapted for elastic fluid pumps · CPC title

• Y10T29/49336

  Blade making · CPC title