# US 9,518,475 B2 · Re-use of internal cooling by medium in turbine hot gas path components > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 9,518,475 B2 - Document ID: US9518475B2 - Status: Granted - Kind: B2 - Application number: 14/064,918 - Filed: 2013-10-28 - Published: 2015-04-30 - Granted: 2016-12-13 - Earliest claimed: 2013-10-28 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: David Wayne Weber; Gregory Thomas Foster; Aaron Ezekiel Smith - Web page: https://patentgrep.com/patent/US9518475B2 ## CPC - F01D 11/24: by selectively cooling-heating stator or rotor components - F01D 9/04: forming ring or sector - F01D 11/005: {Sealing means between non relatively rotating elements} - F05D 2240/11: Shroud seal segments - F05D 2240/81: Cooled platforms - F05D 2260/205: Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes - 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 ## Abstract In one example, an arcuate segment for a ring-shaped, rotary machine component such as a stator nozzle or bucket shroud, includes a segment body having an end face formed with a circumferentially-facing seal slot adapted to receive a seal extending between the segment body and a corresponding seal slot in an adjacent segment body to seal a radially-extending gap between the adjacent segment bodies. A cooling channel is provided in the segment body in proximity to the seal slot, and is adapted to be supplied with cooling air. A passage extends from the cooling channel into the seal slot, at a location where the cooling air can be supplied to the higher pressure area on the radially-outer side of the seal. ## Claims ### Claim 1 An arcuate segment for a ring-shaped, rotary machine component comprising: a segment body having an end face formed with a circumferentially-facing seal slot adapted to receive a seal extending between said segment body and a corresponding seal slot in an adjacent segment body to seal a radially-extending gap between the adjacent segment bodies, and wherein, in use, the seal separates relatively higher and lower pressure areas in the radially-extending gap, on radially outer and radially inner sides respectively, of the seal; a cooling channel provided in said segment body in proximity to said seal slot, adapted to be supplied with cooling air; and a passage extending from said cooling channel into said seal slot at a location enabling supply of cooling air to the higher pressure area on said radially-outer side of said seal; wherein said cooling channel includes a radially inward wall and a radially outward wall, said radially inward wall and said radially outward wall are both radially outward of a radially inner surface of said segment body that is exposed to a hot air path, and said radially inward wall and radially outward wall of said cooling channel are both radially inward of said seal slot. ### Claim 2 (depends on 1) The segment of claim 1 wherein said passage opens on an axial edge of said seal slot. ### Claim 3 (depends on 2) The segment of claim 2 wherein said passage terminates at one or more plenums spaced along said axial edge. ### Claim 4 (depends on 1) The segment of claim 1 wherein said rotary machine component comprises a turbine stator nozzle shroud. ### Claim 5 (depends on 1) The segment of claim 1 wherein said rotary machine component comprises a turbine stator bucket shroud. ### Claim 6 An annular turbine component comprising: plural arcuate segments arranged to form a complete annular ring, each arcuate segment having end faces provided with seal slots; a seal extending between seal slots of adjacent segments sealing a radially oriented gaps between the arcuate segments; a channel provided in each segment in proximity to at least one of said seal slots, and adapted to be supplied with cooling air; and a passage extending from said channel and opening into said at least one seal slot on a radially-outer, high-pressure side of the seal; wherein said channel includes a radially inward wall and a radially outward wall, said radially inward wall and said radially outward wall are both radially outward of a radially inner surface of said arcuate segments that is exposed to a hot air path, said radially inward wall and radially outward wall of said cooling channel are both radially inward of said seal slot. ### Claim 7 (depends on 6) The annular turbine component of claim 6 wherein said plural arcuate segments combine to form an annular turbine stator nozzle shroud. ### Claim 8 (depends on 6) The annular turbine component of claim 6 wherein said plural arcuate segments combine to form an annular turbine stator bucket shroud. ### Claim 9 (depends on 6) The annular turbine component of claim 6 wherein said plural arcuate segments combine to form an annular row of buckets on a turbine rotor wheel, said end faces comprising bucket platform edges. ### Claim 10 (depends on 6) The annular turbine component of claim 6 wherein said passage terminates at one or more plenums spaced along a base of said at least one seal slot. ### Claim 11 (depends on 6) The annular turbine component of claim 6 wherein said passage terminates in said at least one seal slot, along an offset shoulder adapted to prevent said seal from blocking said passage. ### Claim 12 A gas turbine stator comprising: first and second axially adjacent, annular shrouds having opposed end faces provided with respective seal slots; wherein a circumferential, axially-extending gap is formed between said opposed end faces; a circumferential seal seated in said respective seal slots to thereby seal said axially-extending gap, said seal, in use, separating relatively higher and lower pressure areas on radially-outer and radially-inner sides thereof; and one or more cooling channels provided within each of said first and second axially-adjacent, annular shrouds adapted to be supplied with cooling air, said one or more cooling channels arranged to introduce cooling air into a respective one of said seal slots in the relatively higher pressure area on said radially-outer side of said seal; wherein said one or more cooling channels includes a radially inward wall and a radially outward wall, said radially inward wall and said radially outward wall are both radially outward of a radially inner surface of said shrouds that is exposed to a hot air path, and said radially inward wall and radially outward wall of the one or more cooling channels are both radially inward of said seal slot. ### Claim 13 (depends on 12) The gas turbine component of claim 12 wherein said one or more cooling channels communicate with a plurality of plenums spaced along an axially-facing edges of said respective seal slots. ### Claim 14 (depends on 12) The gas turbine component of claim 12 wherein said one or more cooling channels communicate with said respective seal slots along offset shoulders provided along axially-facing edges of said respective seal slots. ### Claim 15 (depends on 12) The gas turbine component of claim 12 wherein said first annular shroud comprises a stator nozzle shroud. ### Claim 16 (depends on 15) The gas turbine component of claim 15 wherein said second annular shroud comprises a stator bucket shroud. ### Claim 17 (depends on 12) The gas turbine component of claim 12 wherein each of said first and second annular shrouds is comprised of plural arcuate segments.