# US 2019/0376404 A1 · Turbine shroud with forward case and full hoop blade track > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2019/0376404 A1 - Document ID: US20190376404A1 - Status: Published application - Kind: A1 - Application number: 16/534,468 - Filed: 2019-08-07 - Published: 2019-12-12 - Earliest claimed: 2016-07-22 - Assignees: Rolls-Royce North American Technologies Inc. - Applicants: Rolls-Royce North American Technologies, Inc. - Inventors: Edward C. Rice; Daniel K. Vetters - Web page: https://patentgrep.com/patent/US20190376404A1 ## CPC - F01D 11/08: for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) - F01D 25/005: {Selecting particular materials} - 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}) - F05D 2220/32: in gas turbines - F05D 2230/60: Assembly methods - F05D 2230/642: using maintaining alignment while permitting differential dilatation - F05D 2240/11: Shroud seal segments - F05D 2240/12: Fluid guiding means, e.g. vanes - F05D 2240/14: Casings or housings protecting or supporting assemblies within - F05D 2260/36: by a form fit connection, e.g. by interlocking - F05D 2300/6033: Ceramic matrix composites [CMC] - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - 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 turbine shroud assembly arranged around a turbine wheel assembly. The turbine shroud assembly includes an annular turbine case, a blade track, and a forward case. The turbine case is arranged around a central axis of the turbine assembly. The blade track is located radially between the turbine case and the central axis. The forward case is coupled to the turbine case and is arranged to block axial movement of the blade track relative to the turbine case. ## Claims ### Claim 1 A turbine assembly for a gas turbine engine, the turbine assembly comprising a turbine case arranged around an axis, a full hoop blade track comprising ceramic matrix composite materials located radially between the turbine case and the axis, the blade track having a leading edge and a trailing edge axially spaced apart from the leading edge, a metallic carrier arranged circumferentially around the blade track to define a chamber located radially between the carrier and the blade track, and a metallic forward case coupled with the turbine case and interlocked with the leading edge of the blade track to block circumferential and axial movement of the blade track relative to the turbine case while allowing radial movement of the blade track relative to the turbine case. ### Claim 2 (depends on 1) The turbine assembly of claim 1, wherein the forward case includes an axial runner that extends from a first end to a second end axially spaced from the first end and a locator flange coupled to the axial runner toward the second end, the locator flange extends radially inwardly away from the turbine case toward the axis, and the locator flange interlocks with the leading edge of the blade track. ### Claim 3 (depends on 2) The turbine assembly of claim 2, wherein the locator flange is formed to include a cutouts that extends radially outwardly into the locator flange, the leading edge of the blade track is formed to include a tang that extends axially forward away from the leading edge of the blade track toward the locator flange, and the tang is received by the cutout formed in the locator flange of the forward case to interlock the forward case and the blade track. ### Claim 4 (depends on 3) The turbine assembly of claim 3, wherein the blade track includes a radial outer surface that faces the turbine case and a radial inner surface radially spaced apart from the radial outer surface and the radial outer surface of the blade track is formed without bores. ### Claim 5 (depends on 2) The turbine assembly of claim 2, wherein the axial runner is formed to define a plurality of apertures that extends radially through the axial runner and the carrier is formed to define an aperture that extends radially through the carrier. ### Claim 6 (depends on 1) The turbine assembly of claim 1, further comprising a seal engaged with the carrier and the blade track, the carrier is formed to define a cooling aperture that extends radially through the carrier, and the forward case is formed to include a plurality of apertures that extend radially through the forward case to cause the forward case to be less rigid. ### Claim 7 (depends on 1) The turbine assembly of claim 1, wherein the forward case includes a first end, a second end axially spaced apart from the first end, an axial runner that extends between the first and second ends, and a locator flange that extends radially inwardly away from the axial runner toward the axis, the axial runner includes a band that extends between the first and second ends of the forward case, a mount flange that extends radially outwardly away from the band at the first end of the forward case, and a shoulder that extends radially outwardly away from the band at the second end of the forward case. ### Claim 8 (depends on 7) The turbine assembly of claim 7, wherein the turbine case includes a forward mount and an aft mount spaced apart axially from the forward mount, the aft mount includes a radial inner surface that faces the axis, and the shoulder of the axial runner has an outer diameter that is larger than an inner diameter of the radial inner surface of the aft mount. ### Claim 9 (depends on 7) The turbine assembly of claim 7, wherein the shoulder is formed to include radially extending scallops arranged to allow air flow between the shoulder and the turbine case. ### Claim 10 A turbine assembly for a gas turbine engine, the turbine assembly comprising a turbine case arranged around an axis, a blade track having a leading edge, a trailing edge axially spaced apart from the leading edge, and a tang that extends axially forward away from the leading edge, and a forward case that includes an axial runner coupled with the turbine case and a locator flange that extends radially inward away from the axial runner, the locator flange formed to define a cutout that extends radially outward into the locator flange, and the tang included in the blade track being located in the cutout. ### Claim 11 (depends on 10) The turbine assembly of claim 10, further comprising a carrier arranged circumferentially around the blade track and formed to define a chamber that opens radially inwardly toward the blade track. ### Claim 12 (depends on 11) The turbine assembly of claim 11, further comprising a first vane assembly engaged with the locator flange included in the forward case to transmit force loads from the first vane assembly to the turbine case through the forward case. ### Claim 13 (depends on 12) The turbine assembly of claim 12, further comprising a second vane assembly located aft of the carrier and configured to engage with the blade track to limit axial movement of the blade track. ### Claim 14 (depends on 10) The turbine assembly of claim 10, wherein the forward case includes mount flange coupled with the turbine case, a band that extends axially away from the mount flange and is spaced apart from the turbine case, and a shoulder that extends radially away from the band and engages the turbine case. ### Claim 15 (depends on 14) The turbine assembly of claim 14, further comprising a carrier arranged circumferentially around the blade track and formed to define a chamber that opens radially inwardly toward the blade track and a seal engaged with the carrier and the blade track. ### Claim 16 (depends on 10) The turbine assembly of claim 10, wherein the blade track is formed without back side bores that extend radially inward into the blade track. ### Claim 17 A method comprising providing an annular turbine case arranged around an axis, a full hoop blade track having a leading edge and a trailing edge axially spaced apart from the leading edge, a forward case having an axially extending axial runner and a radially inwardly extending locator flange, and a carrier arranged to define an inwardly facing chamber, locating the carrier circumferentially around the blade track so that the inwardly facing chamber is aligned axially with the blade track, fastening the axial runner of the forward case to the turbine case, and interlocking the leading edge of a blade track with the locator flange of the forward case. ### Claim 18 (depends on 17) The method of claim 17, further comprising press-fitting the axial runner of the forward case to the turbine case. ### Claim 19 (depends on 17) The method of claim 17, wherein the locator flange is formed to include a cutout and the leading edge of the blade track is formed to include a tang that extends axially away from the leading edge of the blade track toward the forward case and the step of interlocking the leading edge of the blade track with the locator flange of the forward case includes the steps of aligning circumferentially the tang of the blade track with the cutout formed in the locator flange and moving the blade track axially relative to the locator flange to cause the tang to be received in the cutout. ### Claim 20 (depends on 17) The method of claim 17, further comprising directing cooling air through an aperture in the carrier into the inwardly facing chamber.