Gasket for turbine engine and turbine mount assembly
OwnerPhil Wilsoninventor
Life of this patent
Estimating the term…
Abstract
A gasket comprising at least one spacer and configured to prevent contact between a mount link of a turbine mount assembly and a turbine frame mount of an aircraft engine, which is a turbine engine in some embodiments, is provided. The at least one spacer includes a pin cutout to receive a turbine frame pawl pin of the engine mount and a pin groove that is expandable so as to enable the turbine frame pawl pin to pass through and into the pin cutout. The gasket may include a grommet for receiving a connecting ring that is coupled to a streamer grommet of a streamer. The streamer may act as an identifier for the gasket.
Claims20
A gasket comprising:
- a first spacer having a first pin cutout and a first pin groove connected to the first pin cutout;
- a second spacer having a second pin cutout and a second pin groove connected to the second pin cutout;
- and
- a connector coupling the first spacer to the second spacer,
- wherein the first pin groove and the second pin groove are each expandable to enable a turbine frame pawl pin to pass through and into each of the first pin groove and the second pin groove, and
- wherein the first spacer and the second spacer are each positioned between a mount link of a turbine mount assembly and a turbine frame mount of a turbine.
A system comprising:
- a first spacer comprising:
- a first pin cutout comprising a first circular aperture, and
- a first pin groove connected to the first pin cutout, the first spacer having a circular shape with a flat portion adjacent to opposite sides of the first pin groove, the first pin groove having a first distance that is less than a first diameter of the first pin cutout;
- and
- a second spacer comprising:
- a second pin cutout comprising a second circular aperture, and
- a second pin groove connected to the second pin cutout, the second spacer having a circular shape with a flat portion adjacent to opposite sides of the second pin groove, the second pin groove having a second distance that is less than a second diameter of the second pin cutout,
- wherein the first spacer is positioned between a first side of a mount link of a turbine mount assembly and a turbine frame mount of a turbine and the second space is positioned between a second side of the mount link and the turbine frame mount.
A method for installing a gasket onto a turbine comprising:
- removing a turbine from an aircraft via a turbine mount assembly, the turbine having a turbine frame mount extending from a turbine frame and the turbine mount assembly having a mount link coupled to the turbine frame mount via a turbine frame pawl pin;
- installing a first spacer onto the turbine frame pawl pin and between the mount link and a first flange of the turbine frame mount, wherein the first spacer includes a first pin cutout to receive the turbine frame pawl pin and a first pin groove that is configured to expand to enable the turbine frame pawl pin to pass through the first pin groove and into the first pin cutout;
- and
- installing a second spacer onto the turbine frame pawl pin and between the mount link and a second flange of the turbine frame mount, wherein the second spacer includes a second pin cutout to receive the turbine frame pawl pin and a second pin groove that is configured to expand to enable the turbine frame pawl pin to pass through the second pin groove and into the second pin cutout.
Dependencies are inferred from the claim text.