# US 9,038,367 B2 · Fan case thrust reverser > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 9,038,367 B2 - Document ID: US9038367B2 - Status: Granted - Kind: B2 - Application number: 13/234,213 - Filed: 2011-09-16 - Published: 2013-03-21 - Granted: 2015-05-26 - Earliest claimed: 2011-09-16 - Assignees: United Technologies Corporation - Applicants: Gabriel L. Suciu; Brian D. Merry; Allan R. Penda; Christopher M. Dye; Jay Bhatt - Inventors: Gabriel L. Suciu; Brian D. Merry; Allan R. Penda; Christopher M. Dye; Jay Bhatt - Web page: https://patentgrep.com/patent/US9038367B2 ## CPC - F02K 1/70: using thrust reverser flaps or doors mounted on the fan housing - F02K 1/1207: {of one series of flaps hinged at their upstream ends on a fixed structure (F02K1/1215 - F02K1/1292 take precedence)} - F02K 1/72: the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow - 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)} - F02K 1/12: by means of pivoted flaps - F05D 2220/36: specially adapted for the fan of turbofan engines - F05D 2250/25: helical - F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00) - 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 ## Abstract A fan case of a gas turbine engine includes a fan blade containment section defined about an engine axis, a thrust reverser cascade section downstream of the blade containment section and a Fan Exit Guide Vane section downstream of the thrust reverser cascade section. ## Claims ### Claim 1 A fan case of a gas turbine engine comprising: a fan blade containment section defined about anengine axis; a thrust reverser cascade section downstream of said blade containment section, said thrust reverser cascade section including an array of cascade airfoils and a plurality of inner thrust reverser doors radially inwards of said array of cascade airfoils, said inner thrust reverser doors opening inwards toward said engine axis and being arranged in a helix; and a Fan Exit Guide Vane section downstream of said thrust reverser cascade section. ### Claim 2 (depends on 1) The fan case as recited in claim 1, wherein said fan blade containment section includes an abradable layer. ### Claim 3 (depends on 1) The fan case as recited in claim 1, wherein said thrust reverser cascade section includes a multiple of ribs which support a multiple of cascade airfoils. ### Claim 4 A fan section of a gas turbine engine comprising: a fan case defined about an engine axis; a multiple of Fan Exit Guide Vanes attached to said fan case; and a thrust reverser cascade section upstream of said multiple of Fan Exit Guide Vanes, said thrust reverser cascade section including an array of cascade airfoils arranged among a plurality of ribs that are in a helix arrangement and a plurality of inner thrust reverser doors radially inwards of said array of cascade airfoils, said inner thrust reverser doors opening inwards toward said engine axis and being arranged in a helix. ### Claim 5 (depends on 4) The fan section as recited in claim 4, wherein at least one of said multiple of Fan Exit Guide Vanes supports a fan blocker door. ### Claim 6 (depends on 4) The fan section as recited in claim 4, wherein each of said multiple of Fan Exit Guide Vanes supports a fan blocker door. ### Claim 7 (depends on 4) The fan section as recited in claim 4, further comprising a plurality of outer thrust reverser doors radially outwards of said array of cascade airfoils, wherein said plurality of outer thrust reverser doors axially slide generally parallel to said engine axis. ### Claim 8 A gas turbine engine comprising: a fan case defined about an engine axis; a core case defined about said engine axis; a multiple of Fan Exit Guide Vanes attached to said fan case and said core case; a thrust reverser cascade section upstream of said multiple of Fan Exit Guide Vanes, said thrust reverser cascade section including an array of cascade airfoils, a plurality of inner thrust reverser doors radially inwards of said array of cascade airfoils, said inner thrust reverser doors opening inwards toward said engine axis and being arranged in a helix, and said array of cascade airfoils being arranged among a plurality of ribs that are in a helix arrangement. ### Claim 9 (depends on 8) The gas turbine engine as recited in claim 8, further comprising a fan nacelle mounted to said fan case, said fan nacelle at least partially defined by a multiple of outer thrust reverser doors. ### Claim 10 (depends on 8) The gas turbine engine as recited in claim 8, further comprising a multiple of outer thrust reverser doors that axially slide generally parallel to said engine axis. ### Claim 11 (depends on 8) The gas turbine engine as recited in claim 8, further comprising a multiple of outer thrust reverser doors that hinge about an outer door axis generally parallel to said engine axis. ### Claim 12 (depends on 1) The fan case as recited in claim 1, wherein said inner thrust reverser doors are pivotable about respective inner door axes that are inclined to said engine axis. ### Claim 13 (depends on 12) The fan case as recited in claim 12, wherein said array of cascade airfoils is arranged with respect to a plurality of cascade ribs that are also arranged in a helix. ### Claim 14 (depends on 13) The fan case as recited in claim 13, further comprising a plurality of outer thrust reverser doors radially outwards of said array of cascade airfoils. ### Claim 15 (depends on 14) The fan case as recited in claim 14, wherein said plurality of outer thrust reverser doors are pivotable about respective outer door axes that are substantially parallel to the engine axis. ### Claim 16 (depends on 14) The fan case as recited in claim 14, wherein said plurality of outer thrust reverser doors are passively deployable in response to a thrust reverse airflow. ### Claim 17 (depends on 16) The fan case as recited in claim 16, wherein said plurality of outer thrust reverser doors are biased toward a closed position in absence of the thrust reverse airflow. ### Claim 18 (depends on 4) The fan section as recited in claim 4, wherein the plurality of inner thrust reverser doors are pivotable about respective inner door axes that are inclined to said engine axis. ### Claim 19 (depends on 18) The fan section as recited in claim 18, further comprising a plurality of outer thrust reverser doors radially outwards of said array of cascade airfoils, wherein said plurality of outer thrust reverser doors are pivotable about respective outer door axes that are substantially parallel to the engine axis. ### Claim 20 (depends on 19) The fan section as recited in claim 19, wherein said plurality of outer thrust reverser doors are passively deployable in response to a thrust reverse airflow.