# US 10,502,233 B2 · System for an inlet guide vane shroud and baffle assembly > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,502,233 B2 - Document ID: US10502233B2 - Status: Granted - Kind: B2 - Application number: 15/336,831 - Filed: 2016-10-28 - Published: 2017-07-06 - Granted: 2019-12-10 - Earliest claimed: 2016-01-04 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: Marcin Jacek Lobocki; Wiktor Karol Wardecki; Joseph Charles Kulesa; Maciej Staszewski - Web page: https://patentgrep.com/patent/US10502233B2 ## CPC - F01D 11/001: {for sealing space between stator blade and rotor} - F04D 29/542: {Bladed diffusers (fixing blades to stators F01D9/042)} - F01D 5/082: {on the side of the rotor disc} - F01D 9/04: forming ring or sector - F01D 11/00: Preventing or minimising internal leakage of working-fluid, e.g. between stages (sealings in general F16J {; sealing arrangements for transition ducts of combustor cans F01D9/023}) - F01D 11/08: for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) - F01D 17/162: {for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence)} - F01D 25/246: {Fastening of diaphragms or stator-rings} - F02C 3/04: having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) - F02C 7/04: Air intakes for gas-turbine plants or jet-propulsion plants - F04D 29/083: {especially adapted for elastic fluid pumps} - F04D 29/325: {for axial flow fans (blade mountings F04D29/34, blades F04D29/38)} - F05D 2220/32: in gas turbines - F05D 2240/126: Baffles or ribs - F05D 2240/35: Combustors or associated equipment - F05D 2240/80: Platforms for stationary or moving blades - F05D 2250/712: concave - F05D 2260/201: by impingement of a fluid - F05D 2260/31: Retaining bolts or nuts - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02) - 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) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A system for an inlet guide vane shroud and baffle assembly includes a shroud. The shroud includes a first end configured to couple to an annular support member of the gas turbine engine, and a second end. The shroud also includes a distal end including an axially aft extending lip, and a seal assembly configured to form a seal with an annular set of rotating teeth on a rotor of the gas turbine engine. The shroud further includes an arcuate shroud body extending between the distal end and the second end. The shroud and baffle assembly also includes a baffle coupled to an aft side of the shroud. The baffle includes a radially outward end coupled to the aft side, a radially inward end coupled to the axially aft extending lip, and an arcuate baffle body extending there between. Both the shroud and the baffle extend circumferentially about a central axis. ## Claims ### Claim 1 A shroud and baffle assembly for a gas turbine engine, the gas turbine engine including a central axis, a fan assembly positioned at a forward end, and an exhaust outlet positioned at an aft end, said shroud and baffle assembly comprising: a shroud comprising a first end configured to couple to an annular support member of the gas turbine engine, a second end, a distal end comprising an axially aft extending lip, wherein said axially aft extending lip comprises a plurality of scallops, each scallop of said plurality of scallops comprising a cut away extending into at least a portion of said axially aft extending lip, said distal end further comprising a seal assembly configured to form a seal with an annular set of rotating teeth on a rotor of the gas turbine engine, said shroud further comprising an arcuate shroud body extending between said distal end and said second end, wherein said shroud extends circumferentially about the central axis; and a baffle coupled to an aft side of said shroud, said baffle comprising a radially outward end coupled to said aft side, a radially inward end coupled to said axially aft extending lip, and an arcuate baffle body extending therebetween, wherein said baffle extends circumferentially about the central axis. ### Claim 2 (depends on 1) The shroud and baffle assembly in accordance with claim 1, wherein said arcuate baffle body is concave with respect to the fan assembly. ### Claim 3 (depends on 1) The shroud and baffle assembly in accordance with claim 1, wherein said distal end extends axially aft from a radially inward end of said arcuate shroud body. ### Claim 4 (depends on 1) The shroud and baffle assembly in accordance with claim 1, wherein said arcuate shroud body is concave with respect to the fan assembly. ### Claim 5 (depends on 1) The shroud and baffle assembly in accordance with claim 1, wherein said axially aft extending lip comprises a shroud bevel formed on a radially inward surface of said axially aft extending lip concave with respect to the fan assembly, said radially inward surface of said axially aft extending lip and each scallop of said plurality of scallops comprising said shroud bevel. ### Claim 6 (depends on 1) The shroud and baffle assembly according to claim 1, wherein a radially outward surface of said shroud is configured to engage at least one inlet guide vane extending radially outward therefrom. ### Claim 7 An inlet guide vane (IGV) assembly for a gas turbine engine, the gas turbine engine including a central axis, a fan assembly positioned at a forward end, and an exhaust outlet positioned at an aft end, said IGV assembly comprising: a shroud comprising a first end configured to couple to an annular support member of the gas turbine engine, a second end, a distal end comprising an axially aft extending lip, said distal end further comprising a seal assembly configured to form a seal with an annular set of rotating teeth on a rotor of the gas turbine engine, said shroud further comprising an arcuate shroud body extending between said distal end and said second end, wherein said shroud extends circumferentially about the central axis; and a baffle coupled to an aft side of said shroud, said baffle comprising a radially outward end coupled to said aft side, a radially inward end coupled to said axially aft extending lip, and an arcuate baffle body extending therebetween, wherein said baffle extends circumferentially about the central axis; and a plurality of IGVs separate from the annular support member, each IGV of said plurality of IGVs coupled to a radially outward surface of said shroud aft of the first end, wherein said radially outward surface is configured to engage at least one IGV of said plurality of IGVs thereto, wherein said plurality of IGVs are arranged radially about the central axis. ### Claim 8 (depends on 7) The IGV assembly in accordance with claim 7, wherein said arcuate baffle body is concave with respect to the fan assembly. ### Claim 9 (depends on 7) The IGV assembly in accordance with claim 7, wherein said distal end extends axially aft from a radially inward end of said arcuate shroud body. ### Claim 10 (depends on 7) The IGV assembly in accordance with claim 7, wherein said arcuate shroud body is concave with respect to the fan assembly. ### Claim 11 (depends on 7) The IGV assembly in accordance with claim 7, wherein said axially aft extending lip comprises a shroud bevel and a plurality scallops, said shroud bevel formed on a radially inward surface of said axially aft extending lip concave with respect to the fan assembly, each scallop of said plurality of scallops comprising a cut away extending into at least a portion of said axially aft extending lip, and said radially inward surface of said axially aft extending lip and each scallop of said plurality of scallops comprising said shroud bevel. ### Claim 12 (depends on 11) The IGV assembly according to claim 11, wherein the radially outward surface of said shroud is configured to engage at least one inlet guide vane extending radially outward therefrom. ### Claim 13 (depends on 7) The IGV assembly in accordance with claim 7, wherein said second end comprises an overhang and a radially outward aft corner, said overhang extending axially aft from said radially outward aft corner. ### Claim 14 A gas turbine engine including a central axis, a fan assembly positioned at a forward end, and an exhaust outlet positioned at an aft end, said gas turbine comprising: a core engine comprising a compressor, a combustor, and a turbine coupled in a serial flow relationship; a power engine comprising a fan and a power turbine coupled together on a common shaft, said power engine coaxial with said core engine; a shroud and baffle assembly comprising: a shroud comprising a first end configured to couple to an annular support member of the gas turbine engine, a second end, a distal end comprising an axially aft extending lip, wherein said axially aft extending lip comprises a plurality of scallops, each scallop of said plurality of scallops comprising a cut away extending into at least a portion of said axially aft extending lip, said distal end further comprising a seal assembly configured to form a seal with an annular set of rotating teeth on a rotor of said gas turbine engine, said shroud further comprising an arcuate shroud body extending between said distal end and said second end; and a baffle coupled to an aft side of said shroud, said baffle comprising a radially outward end coupled to said aft side, a radially inward end coupled to said axially aft extending lip, and an arcuate baffle body extending therebetween, said baffle extending aftward into an annular space of said gas turbine engine; and a plurality of inlet guide vanes (IGVs), each IGV of said plurality of IGVs coupled radially to and between a radially outward surface of said shroud and a radially inward surface of an annular housing of said compressor, wherein said shroud, said baffle, said plurality of IGVs, and said annular housing are arranged circumferentially about the central axis. ### Claim 15 (depends on 14) The gas turbine engine in accordance with claim 14, wherein said arcuate baffle body is concave with respect to the fan assembly. ### Claim 16 (depends on 14) The gas turbine engine in accordance with claim 14, wherein said distal end extends axially aft from a radially inward end of said arcuate shroud body. ### Claim 17 (depends on 14) The gas turbine engine in accordance with claim 14, wherein said arcuate shroud body is concave with respect to the fan assembly. ### Claim 18 (depends on 14) The gas turbine engine in accordance with claim 14, wherein said axially aft extending lip comprises a shroud bevel formed on a radially inward surface of said axially aft extending lip concave with respect to the fan assembly, said radially inward surface of said axially aft extending lip and each scallop of said plurality of scallops comprising said shroud bevel. ### Claim 19 (depends on 18) The gas turbine engine in accordance with claim 18, wherein said radially outward surface of said shroud is configured to engage at least one inlet guide vane extending radially outward therefrom. ### Claim 20 (depends on 18) The gas turbine engine in accordance with claim 18, wherein said second end comprises an overhang and a radially outward aft corner, said overhang extending axially aft from said radially outward aft corner, wherein said overhang covers at least a portion of a radially inward axially boundary of the annular space of said gas turbine engine.