# US 10,480,454 B2 · Bleed flow duct for a turbomachine comprising a passively actuated variable cross section VBV grating > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,480,454 B2 - Document ID: US10480454B2 - Status: Granted - Kind: B2 - Application number: 15/736,636 - Filed: 2016-06-16 - Published: 2018-07-12 - Granted: 2019-11-19 - Earliest claimed: 2015-06-17 - Assignees: Safran Aircraft Engines - Applicants: Safran Aircraft Engines - Inventors: Jean-Frederic Pierre Joseph Bruhat - Web page: https://patentgrep.com/patent/US10480454B2 ## CPC - F02K 3/075: controlling flow ratio between flows - F01D 17/148: {by means of rotatable members, e.g. butterfly valves} - F02C 9/18: by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} - F05D 2220/323: for aircraft propulsion, e.g. jet engines - F05D 2240/129: Cascades, i.e. assemblies of similar profiles acting in parallel - F05D 2300/522: Density - 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) - 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 The invention relates to a hub (2) of an intermediate casing (1) for a bypass turbomachine comprising: —a bleed stream duct (18), —a bleed valve, comprising a mobile door at the inlet orifice to the bleed stream duct (18), —a set of bleed vanes (22) which are mounted with the ability to rotate about a pivot (26) in the bleed stream duct (18) between an open configuration in which a flow of air coming from the inlet orifice (4) passes between the bleed vanes (22) and a closed configuration, the pivot (26) for each bleed vane (22) being closer to its leading edge (BA) than to its trailing edge (BF). ## Claims ### Claim 1 An intermediate casing hub for a bypass turbine engine, said hub comprising: an inner shroud configured to delimit a primary flow space of the primary gas flow of the turbine engine, an outer shroud configured to delimit a secondary flow space of the secondary gas flow of said turbine engine, a discharge stream duct extending between the inner shroud and the outer shroud, said discharge stream duct leading on the one hand into the primary flow space through an inlet opening formed in the inner shroud, and on the other hand into the secondary flow space through an outlet opening formed in the outer shroud, a door that is movable between a closed position, in which the door closes a passage cross-section of the inlet opening, and an open position, in which the door opens a passage cross-section of the inlet opening, and discharge fins comprising a leading edge and a trailing edge opposite the leading edge, said discharge fins being rotatably mounted around a pivot in the discharge stream duct at the outlet opening between an open configuration, in which an air flow from the inlet opening is able to pass between the discharge fins, and a closed configuration, in which the discharge fins block a passage cross-section of the outlet opening, the intermediate casing hub wherein the pivot of each discharge fin is closer to its leading edge than to its trailing edge and in that the discharge fins comprise a downstream portion extending between the pivot and the trailing edge and an upstream portion extending between the pivot and the leading edge, the downstream portion and the upstream portion of the discharge fins having a different density. ### Claim 2 (depends on 1) The intermediate casing hub according to claim 1, wherein, in the closed configuration, the discharge fins create a substantially continuous surface. ### Claim 3 (depends on 2) The intermediate casing hub according to claim 2, wherein each discharge fin is in contact with an adjacent discharge fin so as to form the substantially continuous surface. ### Claim 4 (depends on 1) The intermediate casing hub according to claim 1, wherein the downstream portion is hollow. ### Claim 5 (depends on 1) The intermediate casing hub according to claim 1, wherein the inner shroud has a revolution axis and the hub comprises a plurality of discharge fins distributed circumferentially around said axis, at least one portion of said discharge fins having a different density distribution depending on their angular position around the axis. ### Claim 6 (depends on 1) The intermediate casing hub according to claim 1, wherein each discharge fin is equipped with a spring system attached on the one hand to the pivot and on the other hand to the discharge stream duct so as to apply a moment to the discharge fin tending to bring said fin into its open configuration. ### Claim 7 (depends on 1) The intermediate casing hub according to claim 1, further comprising a damping system of the discharge fins. ### Claim 8 (depends on 1) An intermediate casing for a bypass turbine engine comprising an intermediate casing hub according to claim 1. ### Claim 9 (depends on 8) A bypass turbine engine comprising an intermediate casing according to claim 8.