Low profile thermally free blind liner hanger attachment for complex shapes
AssigneeUnited Technologies Corporation
InventorThomas M. Barry
Life of this patent
Estimating the term…
Abstract
A hanger system for connecting components in a gas turbine engine has a first spaced component, a second spaced component arranged a desired distance from the first spaced component, and a plurality of spacers arranged between the first spaced component and the second spaced component. A T-bar having a shaft portion and a crossbar is arranged between the components. 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 bracket is coupled to the second spaced component and substantially encapsulates the crossbar portion of the T-bar.
Claims20
A hanger system for connecting components in a gas turbine engine, the hanger system comprising:
- a 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 shaft portion of the T-bar defines a desired distance;
- a second spaced component arranged adjacent to the crossbar portion of the T-bar at the desired distance from the first spaced component;
- and
- a bracket, wherein the bracket is coupled to the second spaced component and substantially encapsulates the crossbar portion of the T-bar.
A method for connecting components in a gas turbine engine, the method comprising:
- inserting a T-bar having a crossbar portion and a shaft portion through a first spaced component, the shaft portion having a threaded portion at a distal end opposite the crossbar portion;
- attaching a bracket to the second spaced component, the bracket having a slot portion and an indent portion;
- passing the crossbar portion of the T-bar through the slot portion of the bracket, and rotating the T-bar such that the crossbar portion of the T-bar is captured by the indent portion;
- and
- threading a nut onto the threaded portion of the T-bar to attach the T-bar to the first spaced component.
A method of installing a liner in a gas turbine engine, the method comprising:
- affixing a plurality of bracket components to a liner, the bracket components each having a slot and an indent;
- inserting a T-bar into the slot portion of each of the plurality of bracket components, each T-bar having a crossbar portion and a shaft portion, and the shaft portion having a threaded section;
- rotating each of the T-bars such that the T-bar is captured by the indent of the bracket;
- advancing the liner toward a structural component, such that the shaft portion of the T-bars pass through apertures in the structural component;
- and
- threading a nut onto the threaded section of each of the plurality of T-bars.
Dependencies are inferred from the claim text.