# US 2014/0154064 A1 · Thrust reverser device > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2014/0154064 A1 - Document ID: US20140154064A1 - Status: Published application - Kind: A1 - Application number: 14/176,236 - Filed: 2014-02-10 - Published: 2014-06-05 - Earliest claimed: 2011-08-08 - Assignees: Aircelle - Applicants: Aircelle - Inventors: Xavier BOUTEILLER; Patrick BOILEAU; Peter SEGAT - Web page: https://patentgrep.com/patent/US20140154064A1 ## CPC - F02K 1/566: {by blocking the rearward discharge by means of a translatable member} - F02K 1/72: the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - 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) - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A thrust reverser device of a nacelle includes a thrust reversal cowl which moves alternately from a closed position to an open position in which the thrust reversal cowl opens a path within the nacelle and uncovers a flow deflector, and a rear frame supporting deflecting cascades. The flow deflector includes first deflecting cascades distributed over a circumference of the thrust reversal cowl and arranged so that a diverted flow passes, at least in part, through the first deflecting cascades, when the thrust reverser device is in reverse jet. In particular, the rear frame has an extension structure provided with second deflecting cascades which redirect a portion of the diverted flow when the thrust reverser device is in reverse jet. ## Claims ### Claim 1 A thrust reverser device of a nacelle, comprising: a thrust reversal cowl movable in translation and moving alternately from a closed position in which the thrust reversal cowl provides an aerodynamic continuity of the nacelle and covers flow deflecting means, to an open position in which the thrust reversal cowl opens a path within the nacelle and uncovers the flow deflecting means, said flow deflecting means comprising at least one first deflecting cascade distributed over a circumference of the thrust reversal cowl and arranged so that a diverted flow passes, at least in part, through said at least one first deflecting cascade, when the thrust reverser device is in reverse jet; and a rear frame supporting a downstream end of said at least one first deflecting cascade, wherein the rear frame comprises at least an extension structure provided with second deflecting cascades which redirect a portion of the diverted flow when the thrust reverser device is in reverse jet, said extension structure extending said at least one first deflecting cascade. ### Claim 2 (depends on 1) The thrust reverser device according to claim 1, wherein the extension structure of the second deflecting cascades is mounted at the downstream end of the rear frame. ### Claim 3 (depends on 1) The thrust reverser device according to claim 1, wherein the rear frame is mounted downstream of a vane being at the furthest downstream of the at least one first deflecting cascade. ### Claim 4 (depends on 1) The thrust reverser device according to claim 1, wherein the second deflecting cascades are arranged on the circumference of the rear frame. ### Claim 5 (depends on 1) The thrust reverser device according to claim 1, wherein the second deflecting cascades are angularly spaced apart from each other. ### Claim 6 (depends on 1) The thrust reverser device according to claim 1, wherein the second deflecting cascades are adjoined to one another. ### Claim 7 (depends on 1) The thrust reverser device according to claim 1, wherein the second deflecting cascades extend parallel to a sliding axis of the thrust reversal cowl. ### Claim 8 (depends on 1) The thrust reverser device according to claim 1, wherein the second deflecting cascades are obliquely oriented relative to a sliding axis of the thrust reversal cowl. ### Claim 9 (depends on 1) The thrust reverser device according to claim 1, wherein the second deflecting cascades are fixed independently relative to said at least one first deflecting cascade. ### Claim 10 (depends on 1) The thrust reverser device according to claim 1, wherein the second deflecting cascades are movable in translation independently relative to at least one of the first deflecting cascades and the thrust reversal cowl during the thrust reversal cowl's displacements between the closed and open positions. ### Claim 11 (depends on 1) The thrust reverser device according to claim 1, wherein the rear frame releases at least one space between the second deflecting cascades to accommodate at least one of actuating means and guiding means of the thrust reversal cowl. ### Claim 12 (depends on 1) The thrust reverser device according to claim 1, wherein the rear frame and the at least one first deflecting cascade comprise complementary snap means. ### Claim 13 (depends on 1) A nacelle of a turbofan engine comprising a thrust reverser device according to claim 1.