Tank assembly
AssigneeROLLS-ROYCE plc
InventorDavid A. Edwards
Life of this patent
Estimating the term…
Abstract
A tank assembly (100) for a gas turbine engine is provided comprising a tank (102) and a plurality of restraints (112, 114). The restraints (112, 114) include a fixing part (124) for securing the tank (102) to a support structure (104). A first restraint (112) has a first rigidity in the direction of a length of the tank (102) and at least one second restraint (114) has a second rigidity in the direction of the length of the tank (102). Upon thermal expansion or contraction of the tank (102) relative to the support structure (104), the or each second restraint (114) flexes to a greater extent than the first restraint (112).
Claims19
A tank assembly for a gas turbine engine, the tank assembly comprising:
- a tank;
- and
- a plurality of restraints spaced apart along a length of the tank, each including a fixing part for securing the tank to a support structure, the plurality of restraints including a first restraint and at least one second restraint;
- wherein the first restraint has a first rigidity in a direction along the length of the tank;
- the or each second restraint has a second rigidity in a direction along the length of the tank that is less than the first rigidity;
- each restraint is connected to the tank over a connected extent;
- and
- the restraints each include two side portions, each of the side portions including the connected extent and an unconnected extent that is not directly connected to the tank,
- wherein the plurality of restraints are substantially U-shaped, including a top portion and two side portions, and extend around top and side surfaces of the tank.
A tank assembly for a gas turbine engine, the tank assembly comprising:
- a tank;
- and
- a plurality of restraints spaced apart along a length of the tank, each including a fixing part for securing the tank to a support structure, the plurality of restraints including a first restraint and at least one second restraint;
- wherein the first restraint has a first rigidity in a direction along the length of the tank;
- the or each second restraint has a second rigidity in a direction along the length of the tank that is less than the first rigidity;
- each restraint is connected to the tank over a connected extent;
- and
- the restraints each include two side portions, each of the side portions including the connected extent and an unconnected extent that is not directly connected to the tank,
- wherein two second restraints are positioned at or towards opposing ends of the tank and the first restraint is interposed between the two second restraints.
A gas turbine engine for an aircraft, the gas turbine engine comprising:
- an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor;
- a fan located upstream of the engine core, the fan comprising a plurality of fan blades;
- a support structure;
- and
- a tank assembly, the tank assembly comprising:
- a tank;
- and a plurality of restraints spaced apart along a length of the tank, each including a fixing part for securing the tank to a support structure, the plurality of restraints including a first restraint and at least one second restraint;
- wherein the first restraint has a first rigidity in a direction along the length of the tank;
- the or each second restraint has a second rigidity in a direction along the length of the tank that is less than the first rigidity;
- each restraint is connected to the tank over a connected extent;
- and
- the restraints each include two side portions, each of the side portions including the connected extent and an unconnected extent that is not directly connected to the tank, the tank assembly being secured to the support structure by the fixing part,
- wherein the plurality of restraints extend around top and side surfaces of the tank.
Dependencies are inferred from the claim text.