Cooling passages for a mid-turbine frame
AssigneeUnited Technologies Corporation
InventorsAnthony P. Cherolis, Jeffrey J. Lienau, Robert Newman, Cheng-Zhang Wang
Life of this patent
Estimating the term…
Abstract
A gas turbine engine includes a mid-turbine frame that includes an inner frame case. At least one spoke is connected to the inner frame case. At least one spoke includes a fluid passage that is in fluid communication with a channel on a radially inner end of the fluid passage. The channel is directed in a radially inward and circumferential direction. A cavity is located radially inward from the mid-turbine frame and is in fluid communication with the channel.
Claims13
A gas turbine engine comprising:
- a mid-turbine frame including:
- an inner frame case;
- and
- at least one spoke connected to the inner frame case, wherein the at least one spoke includes a fluid passage in fluid communication with a channel on a radially inner end of the fluid passage, the channel located in a plug separate from the at least one spoke, the plug contacting the at least one spoke and adjacent to the inner frame case, the plug including a conical portion tapering to the channel;
- and
- a cavity located radially inward from the mid-turbine frame in fluid communication with the channel;
- and
- wherein an outlet of the channel directs a fluid into the cavity circumferentially relative to a longitudinal axis of a gas turbine shaft.
A mid-turbine frame in a gas turbine engine comprising:
- a hollow spoke including a fluid passage in fluid communication with a channel on a radially inner end of the fluid passage, wherein the channel is located in a plug separate from the hollow spoke, the plug contacting the hollow spoke, adjacent to an inner frame case, and located radially outward from the inner frame case relative to a longitudinal axis of the gas turbine engine;
- and
- the inner frame case at least partially defining a cavity radially inward from the inner frame case, wherein the channel is in fluid communication with the cavity and the hollow spoke is directly connected to the inner frame case and the channel includes a cylindrical cross section located in the plug and the plug includes a conical portion tapering to the channel.
A method of cooling a portion of a gas turbine engine comprising:
- directing cooling airflow through a hollow spoke in a mid-turbine frame, the hollow spoke including a fluid passage in fluid communication with a channel on a radially inner end of the fluid passage, the channel located in a plug separate from the hollow spoke, the plug contacting the hollow spoke and adjacent to an inner frame case, the plug including a conical portion tapering to the channel;
- and
- directing the cooling airflow into a cavity on a radially inner end of the hollow spoke, wherein an outlet of the channel directs the cooling airflow into the cavity circumferentially relative to a longitudinal axis of the gas turbine engine.
Dependencies are inferred from the claim text.