Liner hanger cable
AssigneeUnited Technologies Corporation
InventorDonald W. Peters
Life of this patent
Estimating the term…
Abstract
A liner for a gas turbine engine includes a liner defining an inner surface exposed to exhaust gases and a duct spaced radially outward of the liner. A plurality of hanger assemblies is disposed within the radial space between the liner and the duct for supporting the liner relative to the duct. Each of the hanger assemblies includes a cable having a first end attached to the duct and a second end attached to the liner.
Claims18
A liner assembly for a gas turbine engine comprising:
- a liner disposed about an engine axis, the liner defining an inner surface exposed to exhaust gases;
- a duct spaced radially outward of the liner;
- and
- a hanger assembly supporting the liner relative to the duct, the hanger assembly including a cable extending transverse to the engine axis and having a first end attached to the duct and a second end attached to the liner, wherein the cable restricts relative radial movement between the liner and duct along a longitudinal length of the cable in only one direction.
A gas turbine engine comprising:
- a fan section including a plurality of fan blades rotatable about an axis;
- a compressor section in communication with the fan section;
- a combustor in fluid communication with the compressor section;
- a turbine section in fluid communication with the combustor and driving the fan section and the compressor section;
- and
- an exhaust liner aft of the turbine section, the exhaust liner including a liner defining an inner surface exposed to exhaust gases, a duct spaced radially outward of the liner;
- and
- a hanger assembly supporting the liner relative to the duct, the hanger assembly including a cable having a first end attached to the duct and a second end attached to the liner, wherein the hanger assembly restrains relative radial movement between the liner and duct in only one direction along a longitudinal length of the cable.
A hanger assembly for supporting a liner of a gas turbine engine comprising:
- a first end attachable to a support structure;
- a second end distal from the first end, the second end attachable to a liner;
- and
- a cable extending transverse to an engine longitudinal axis between the first end and the second end, the second end including a ball received within a mount on the liner, wherein the cable restrains relative movement of the liner relative to the support structure in one direction along a longitudinal length of the cable.
A method of supporting a liner of a gas turbine engine comprising:
- securing a first end of a cable to the liner transverse to an engine longitudinal axis;
- and
- securing a second end of the cable to a support structure, wherein the first end comprises a ball and the ball is received within a seat defined on the liner.
Dependencies are inferred from the claim text.