# US 12,110,801 B2 · Turbine shroud segment and its manufacture > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,110,801 B2 - Document ID: US12110801B2 - Status: Granted - Kind: B2 - Application number: 18/447,740 - Filed: 2023-08-10 - Published: 2024-05-16 - Granted: 2024-10-08 - Earliest claimed: 2022-08-30 - Assignees: ROLLS-ROYCE plc - Applicants: Rolls-Royce plc - Inventors: Rupert J. Taylor; Ngungunyana Mhlanga; Grant Mathieson; Ryan R. Allen; James Revell; Dinesh Perumalsamy; Carlos Javier Diaz Rodriguez - Web page: https://patentgrep.com/patent/US12110801B2 ## CPC - F01D 11/08: for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) - F01D 25/24: Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) - B22F 5/009: {of turbine components other than turbine blades (of turbine blades B22F5/04)} - B22F 10/68: Cleaning or washing - B33Y 80/00: Products made by additive manufacturing - F01D 9/04: forming ring or sector - F01D 25/12: Cooling - F05D 2230/31: Layer deposition - F05D 2240/11: Shroud seal segments - F05D 2260/20: Heat transfer, e.g. cooling - F05D 2260/201: by impingement of a fluid - F05D 2260/202: by film cooling - F05D 2260/607: Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - B22F: WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER (making alloys by powder metallurgy C22C); APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER - B33Y: ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A turbine shroud segment, e.g. for a gas turbine engine, which is coolable by a supply of cooling air, e.g. from a gas turbine engine compressor. The turbine shroud segment has a segment casing that has a radially outer surface and a radially inner surface. The segment casing houses a main plenum, a first layer of impingement chambers, a second layer of impingement chambers, and a plurality of effusion passages. The first layer of impingement chambers fluidly communicates with the main plenum via transfer passages that are formed in the segment casing. The second layer of impingement chambers fluidly communicates with the first layer of impingement chambers via impingement passages that are formed in the segment casing. The effusion passages run between impingement chamber core surface, which is a radially inner surface of an impingement chamber, and the radially inner surface of the segment casing. ## Claims ### Claim 1 A turbine shroud segment for a gas turbine engine that has a supply of cooling air, the turbine shroud segment comprising: a segment casing that has a radially outer surface and a radially inner surface; the segment casing houses a main plenum, a first layer of impingement chambers, a second layer of impingement chambers, and a plurality of effusion passages; the first layer of impingement chambers fluidly communicates with the main plenum via transfer passages that are formed in the segment casing; the second layer of impingement chambers fluidly communicates with the first layer of impingement chambers via impingement passages that are formed in the segment casing; and the effusion passages run between impingement chamber core surface, which is a radially inner surface of an impingement chamber, and the radially inner surface of the segment casing; wherein in use the main plenum receives cooling air from the supply of cooling air, the cooling air passes through the transfer passages to the first layer of impingement chambers, then through the impingement passages into the second layer of impingement chambers, and then through the effusion passages that open onto the radially inner surface of the segment casing; wherein the segment casing has a cooling system inlet that is formed in a side of the segment casing to provide access to a particle separator that is configured to guide lower mass particles suspended in cooling air into the main plenum via a primary passage and guide higher mass particles suspended in cooling air into and along a dust passage in the segment casing that exits the segment casing via a dust outlet; and wherein the particle separator is swan-necked. ### Claim 2 (depends on 1) The turbine shroud segment of claim 1, wherein the segment casing houses a single main plenum, the first layer of impingement chambers comprises four to forty impingement chambers, and the second layer of impingement chambers comprises four to forty impingement chambers. ### Claim 3 (depends on 2) The turbine shroud segment of claim 2, wherein the segment casing houses a single main plenum, the first layer of impingement chambers comprises six to thirty impingement chambers, and the second layer of impingement chambers comprises six to thirty impingement chambers. ### Claim 4 (depends on 1) The turbine shroud segment of claim 1, wherein the casing segment has a wall that extends into the particle separator to bifurcate cooling air flow between the primary passage and the dust passage. ### Claim 5 (depends on 1) The turbine shroud segment of claim 1, wherein the effusion passages have a circular, elliptical or square cross-section. ### Claim 6 (depends on 1) The turbine shroud segment of claim 1, wherein the cross-section of the effusion passages is uniform along their length. ### Claim 7 (depends on 1) The turbine shroud segment of claim 1, wherein the effusion passages are angled with respect to the radially inner surface of the segment casing. ### Claim 8 (depends on 7) The turbine shroud segment of claim 7, wherein the effusion passages are angled at 1 to 15 o with respect to the radially inner surface of the segment casing. ### Claim 9 (depends on 1) The turbine shroud segment of claim 1, wherein the effusion passages are entered via recessed portions in the impingement chamber core surface of the segment casing. ### Claim 10 (depends on 9) The turbine shroud segment of claim 9, wherein a portion of the wall surrounding the entrance of the recessed portions in the impingement chamber core surface is thickened. ### Claim 11 (depends on 1) The turbine shroud segment of claim 1, wherein the effusion passages are curved. ### Claim 12 (depends on 1) The turbine shroud segment of claim 1, wherein the effusion passage has an effusion passage inlet that is formed in the impingement chamber core surface of the turbine shroud segment and an effusion passage outlet that is formed in the radially inner surface of the turbine shroud segment, the effusion passage inlet being rounded to facilitate fluid flow. ### Claim 13 (depends on 1) The turbine shroud segment of claim 1, wherein the transfer passages and/or the impingement passages include powder removal funnels. ### Claim 14 (depends on 13) The turbine shroud segment of claim 13, wherein the powder removal funnels are frustoconical in shape, and/or have a rectangular base. ### Claim 15 (depends on 1) The turbine shroud segment of claim 1, wherein an effusion passage flow collar is located between the impingement chamber and the effusion passage. ### Claim 16 (depends on 1) The turbine shroud segment of claim 1, which is formed as a single unitary component by an additive layer manufacturing process. ### Claim 17 (depends on 1) A gas turbine engine that includes at least one turbine shroud segment according to claim 1. ### Claim 18 (depends on 1) A method for manufacturing a turbine shroud segment, the method comprising forming a turbine shroud segment according to claim 1, by additive layer manufacturing.