Accessible debris separator for high pressure turbine outside diameter fed static components
AssigneeRtx Corporation
InventorsPaul M Lutjen, Jose R Paulino, Tracy A Propheter-Hinckley
Life of this patent
Estimating the term…
Abstract
An accessible debris separator for a gas turbine engine is provided. The accessible debris separator including a chamber formed by a entrance wall, an exit wall, an inner wall, and an outer wall; a plurality of inlet openings in the entrance wall; a plurality of outlet openings in the exit wall; and a component within the chamber, the component forcing cooling air with debris particulates entering the chamber via an inlet opening of the plurality of inlet openings to take a circuitous path thereby separating the debris particulates from the cooling air prior to the cooling air exiting the chamber via an outlet opening of the plurality of outlet openings.
Claims10
An accessible debris separator for a gas turbine engine, the accessible debris separator comprising:
- a chamber formed by an entrance wall, an exit wall, an inner wall, and an outer wall;
- a plurality of inlet openings in the entrance wall;
- a plurality of outlet openings in the exit wall;
- and
- a component within the chamber, the component forcing cooling air with debris particulates entering the chamber via an inlet opening of the plurality of inlet openings to take a circuitous path thereby separating the debris particulates from the cooling air prior to the cooling air exiting the chamber via an outlet opening of the plurality of outlet openings, wherein the component within the chamber is a diverter, the diverter coupled to at least one of the inner wall or the outer wall and extending radially into the chamber past the plurality of inlet openings, wherein the component within the chamber is a set of components, wherein the diverter is a first component of the set of components, and wherein a second component of the set of components is a protrusion, the protrusion protruding opposite the entrance wall into the chamber from the outlet opening of the plurality of outlet openings in the exit wall.
A gas turbine engine comprising:
- a blade outer air seal (BOAS);
- and
- an accessible debris separator positioned forward the BOAS, the accessible debris separator comprising:
- a chamber formed by an entrance wall, an exit wall, an inner wall, and an outer wall;
- a plurality of inlet openings in the entrance wall;
- a plurality of outlet openings in the exit wall;
- and
- a component within the chamber, the component forcing cooling air with debris particulates entering the chamber via an inlet opening of the plurality of inlet openings to take a circuitous path thereby separating the debris particulates from the cooling air prior to the cooling air exiting the chamber via an outlet opening of the plurality of outlet openings, wherein the component within the chamber is a diverter, the diverter coupled to at least one of the inner wall or the outer wall and extending radially into the chamber past the plurality of inlet openings, wherein the component within the chamber is a set of components, wherein the diverter is a first component of the set of components, and wherein a second component of the set of components is a protrusion, the protrusion protruding opposite the entrance wall into the chamber from the outlet opening of the plurality of outlet openings in the exit wall.
Dependencies are inferred from the claim text.