# US 10,309,308 B2 · Cooling passages for a mid-turbine frame > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,309,308 B2 - Document ID: US10309308B2 - Status: Granted - Kind: B2 - Application number: 14/598,732 - Filed: 2015-01-16 - Published: 2016-07-21 - Granted: 2019-06-04 - Earliest claimed: 2015-01-16 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Anthony P. Cherolis; Jeffrey J. Lienau; Robert Newman; Cheng-Zhang Wang - Web page: https://patentgrep.com/patent/US10309308B2 ## CPC - F02C 7/18: the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} - F01D 9/065: {Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26)} - F05D 2220/3213: an intermediate stage of the turbine - F05D 2240/90: Mounting on supporting structures or systems - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00) - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## 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. ## Claims ### Claim 1 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. ### Claim 2 (depends on 1) The gas turbine engine of claim 1, wherein the cavity forms a bearing support cavity and is at least partially defined by the inner frame case and a bearing support member. ### Claim 3 (depends on 2) The gas turbine engine of claim 2, wherein the cavity forms a torque box. ### Claim 4 (depends on 1) The gas turbine engine of claim 1, where the channel extends in a circumferential direction at an angle between 30 and 80 degrees relative to a base portion of the at least one spoke. ### Claim 5 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. ### Claim 6 (depends on 5) The mid-turbine frame of claim 5, wherein the cavity is at least partially defined by the inner frame case and a bearing support member and the cavity forms a torque box. ### Claim 7 (depends on 5) The mid-turbine frame of claim 5, wherein the channel extends in a circumferential direction relative to an a longitudinal axis of the gas turbine engine at an angle between 30 and 80 degrees relative to a base portion of the hollow spoke. ### Claim 8 (depends on 5) The mid-turbine frame of claim 5, wherein an outlet of the channel directs a fluid into the cavity circumferentially relative to a longitudinal axis of the gas turbine engine. ### Claim 9 (depends on 5) The mid-turbine frame of claim 5, wherein a radially inner most surface of the plug contacts a radially outer surface of the inner frame case. ### Claim 10 (depends on 5) The mid-turbine frame of claim 5, wherein a plurality of fasteners extend through the inner frame case into the hollow spoke. ### Claim 11 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. ### Claim 12 (depends on 11) The method of claim 11, wherein the channel extends in a circumferential direction at an angle between 30 and 80 degrees relative to a base portion of the hollow spoke. ### Claim 13 (depends on 11) The method of claim 11, wherein the cavity forms a torque box and is at least partially defined by the inner frame case and a bearing support member.