Thermally free hanger with length adjustment feature
AssigneeUnited Technologies Corporation
InventorsShawn M. McMahon, Jeffrey R. Lavin
Life of this patent
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Abstract
A system for connecting spaced components of a gas turbine engine includes connecting one end of a T-bar to each of the spaced components. One component is attached to the crossbar portion of the T-bar by trapping the crossbar between the component and a bracket. The second component is attached to the shaft portion using a hanger nut connected to the shaft portion of the T-bar and bolted to the second component. The system may be installed by attaching the crossbar portion, then advancing the first component towards the second component until the shaft portion passes through an aperture in the second component. The hanger nut is attached to the shaft portion and the second component.
Claims20
A system for fastening two spaced components in gas turbine engine, the system comprising:
- a first spaced component;
- a second spaced component arranged a desired distance from the first spaced component;
- a T-bar having a shaft portion and a crossbar portion, wherein the shaft portion of the T-bar passes through an aperture in the first spaced component and the crossbar portion of the T-bar is arranged adjacent to the second spaced component;
- a hanger nut configured to capture the shaft portion of the T-bar;
- a cap nut configured to attach the hanger nut and the shaft portion of the T-bar to the first spaced component;
- and
- a bracket, wherein the bracket is coupled to the second spaced component and captures the crossbar portion of the T-bar with sufficient head space to permit limited movement of the crossbar portion.
A method for connecting components in a gas turbine engine, the method comprising:
- arranging a T-bar having a shaft and a crossbar portion such that:
- the shaft portion protrudes through an aperture in a first spaced component;
- and
- the crossbar portion is adjacent to a second spaced component;
- attaching a bracket to the second spaced component to capture the crossbar portion between the second spaced component and the bracket;
- arranging a hanger nut adjacent to the T-bar and the first spaced component, the hanger nut having an aperture, such that the aperture is adjacent to a bolt hole in the first spaced component;
- attaching the hanger nut to the first spaced component by inserting a bolt through the aperture and the bolt hole;
- and
- attaching a cap nut to a threaded portion of the shaft portion of the T-bar.
A method of installing a liner in a gas turbine engine, the method comprising:
- inserting a crossbar portion of a T-bar between a liner and a bracket to substantially encapsulate the crossbar portion between the liner and the bracket, the T-bar including the crossbar portion and an integrally formed shaft portion transecting the crossbar portion at a midsection;
- affixing the bracket to the liner;
- advancing the liner towards a structure, the structure having an aperture, such that a shaft portion of the T-bar passes through the aperture;
- inserting a hanger nut into the aperture, such that the hanger nut circumscribes the shaft portion of the T-bar and is connected to the T-bar by a threaded connection;
- and
- bolting the hanger nut to the structural component.
Dependencies are inferred from the claim text.