Frame junction cooling holes
AssigneeUnited Technologies Corporation
InventorsJonathan Ariel Scott, William Yeager
Life of this patent
Estimating the term…
Abstract
A module for a gas turbine engine comprises a frame and a frame cooling system. The frame includes a circumferentially distributed plurality of radially extending struts. Each strut is joined to an outer frame section at an outer frame junction, and joined to an inner frame section at an inner frame junction. The frame cooling system comprises an inlet, a plurality of cooling air passages extending from the inlet radially through each of the plurality of frame struts; and an outlet. The outlet is in fluid communication with at least one of the cooling air passages and includes a film cooling hole formed through the frame proximate the outer frame junction.
Claims24
A module for a gas turbine engine comprising:
- a frame including a circumferentially distributed plurality of radially extending struts, each strut integrally joined to an outer frame section at an outer frame junction, and integrally joined to an inner frame section at an inner frame junction;
- and
- a frame cooling system comprising:
- an inlet;
- a cooling air passage extending from the inlet radially through one of the plurality of frame radially extending struts;
- a first outlet in fluid communication with the cooling air passage, the first outlet including at least one film cooling hole formed through the frame proximate the outer frame junction, an exit portion of the at least one film cooling hole directed into an outer cooling air cavity toward at least one of an inner surface of the outer frame section, and an outer surface of each strut;
- and
- a second outlet in fluid communication with the cooling air passage, the second outlet including at least one second outlet film cooling hole formed through the frame proximate the inner frame junction, an exit portion of the at least one second outlet film cooling hole directed into an inner cooling air cavity toward at least one of an inner surface of the inner frame section, and an inner side of each strut;
- wherein the cooling air passage is sized to direct more than 50% of cooling air flow in the cooling air passage toward the outer frame section and the outer cooling air cavity.
A gas turbine engine frame comprising:
- an outer case;
- an inner hub;
- a first strut extending radially between the inner hub and the outer case, the first strut integrally joined to the outer case at an outer frame junction, and integrally joined to the inner hub at an inner frame junction;
- and
- a frame cooling system including an inlet, a cooling air passage extending from the inlet radially through the strut, a first outlet in fluid communication with the cooling air passage, the first outlet including at least one film cooling hole formed through at least one circumferential side of the outer frame junction, an exit portion of the at least one film cooling hole directed toward at least one of an inner surface of an outer frame section, and an outer surface of the first strut, and a second outlet in fluid communication with the cooling air passage, the second outlet including at least one second outlet film cooling hole formed through the frame proximate the inner frame junction, an exit portion of the at least one second outlet film cooling hole directed into an inner cooling air cavity toward at least one of an inner surface of the inner frame section, and an inner side of the first strut;
- wherein the cooling air passage is sized to direct more than 50% of cooling air flow in the cooling air passage toward the outer case and the outer cooling air cavity.
Dependencies are inferred from the claim text.