Superplastic forming

Patent metadata

Field	Value
Publication number	US-10480528-B2
Application number	US-201715659128-A
Country	US
Kind code	B2
Filing date	Jul 25, 2017
Priority date	Aug 10, 2016
Publication date	Nov 19, 2019
Grant date	Nov 19, 2019

Abstract

An aerofoil structure with a hollow cavity is manufactured by diffusion bonding and superplastic forming. Outer panels are formed of a first material; a membrane is formed of a second material. Stop-off material is applied to preselected areas on at least one side of the membrane or of one of the panels so as to prevent diffusion bonding between the panels and the membrane at the preselected areas. The panels and the membrane are arranged in a stack and a diffusion bonding process is performed to bond together the first and second panels and the membrane to form an assembly. A superplastic forming process is performed at a forming temperature to expand the assembly to form the aerofoil structure. The forming temperature is selected so that the second material undergoes superplastic deformation at the forming temperature and the first material does not undergo superplastic deformation at the forming temperature.

First claim

The invention claimed is:

1. A method of manufacturing an aerofoil structure by diffusion bonding and superplastic forming to create a substantially hollow cavity within the aerofoil structure, the method comprising the steps of:
providing first and second outer panels formed of a first material;
providing a membrane formed of a second material;
applying stop-off material to preselected areas on at least one side of the membrane or of the first or second panel so as to prevent diffusion bonding between the panels and the membrane at the preselected areas;
arranging the first and second panels and the membrane in a stack so that the membrane is between the first and second panels;
performing a diffusion bonding process to bond together the first and second panels and the membrane to form an assembly;
performing a superplastic forming process at a forming temperature to expand the assembly to form the aerofoil structure with the hollow cavity;
the method characterised in that the forming temperature is selected so that the second material undergoes superplastic deformation at the forming temperature and the first material does not undergo superplastic deformation at the forming temperature.

2. The method of claim 1 , in which the first material undergoes creep deformation at the forming temperature.

3. The method of claim 1 , in which the superplastic temperature range of the first material is higher than the superplastic temperature range of the second material.

4. The method of claim 1 , in which the first material is Ti-6Al-4V and the second material is titanium alloy grade 38.

5. An aerofoil structure formed by diffusion bonding and superplastic forming, the aerofoil structure comprising first and second outer panels formed of a first material and a membrane formed of a second material, characterised in that the second material has undergone superplastic deformation, the first material has not undergone superplastic deformation, and the first and second panels and the membrane are arranged in a stack so that the membrane is between the first and second panels.

6. The aerofoil structure of claim 5 , in which the superplastic temperature range of the first material is higher than the superplastic temperature range of the second material.

7. The aerofoil structure of claim 5 , in which the first material has undergone creep deformation.

Assignees

• Rolls Royce Plc

Inventors

• Halliday Robert
• Wilkinson Stephen J

Classifications

• F04D29/388 Primary

  characterised by construction · CPC title

• B21D53/78

  propeller blades; turbine blades · CPC title

• B21D26/029

  Closing or sealing means · CPC title

• B23P15/02

  turbine or like blades from one piece · CPC title

• B21D26/059

  Layered blanks · CPC title