# US 11,905,885 B2 · Fuel supply circuit for a combustion chamber of a turbomachine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,905,885 B2 - Document ID: US11905885B2 - Status: Granted - Kind: B2 - Application number: 18/248,665 - Filed: 2021-10-05 - Published: 2023-12-21 - Granted: 2024-02-20 - Earliest claimed: 2020-10-14 - Assignees: Safran Aircraft Engines - Applicants: Safran Aircraft Engines - Inventors: Kevin Didier Pierre Le Normand; Frederic Brettes; Loic Pora - Web page: https://patentgrep.com/patent/US11905885B2 ## CPC - F02C 7/222: {Fuel flow conduits, e.g. manifolds} - F02C 7/232: Fuel valves {(control of fuel supply by means of fuel metering valves F02C9/263)}; Draining valves or systems (valves in general F16K) - F02C 7/236: Fuel delivery systems comprising two or more pumps - F23R 3/283: {Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances} - F05D 2250/311: the axes being in line - F23R 3/34: Feeding into different combustion zones - 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) - F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A fuel supply circuit including a supply duct in which a first flow (Fl) is able to circulate, at least one supply pump for circulating the fuel from a tank to a metering unit, and a recirculation duct for a second flow upstream of the pump, wherein the ducts (20, 60) discharge in different directions upstream of the pump; the circuit includes a dispensing device including an internal flow duct for the first flow (Fl), an external flow channel for the second flow and at least one passage orifice for the second flow, which communicates fluidically with the channel; and the at least one orifice (810) and the duct are coaxial and respectively discharge upstream of the pump. ## Claims ### Claim 1 A fuel supply circuit for a combustion chamber of a turbomachine, in particular an aircraft, comprising: a supply channel configured for the circulation of a first fuel flow from a fuel tank; a metering unit configured to provide a predetermined flow rate of fuel into the combustion chamber; at least one supply pump for circulating the fuel from the tank towards the metering unit; a recirculation channel for a second fuel flow, corresponding to a quantity of excess fuel from the metering unit, upstream of the supply pump; the supply and recirculation channels opening in different directions upstream of the supply pump; wherein the circuit comprises a distribution device of at least one of the fuel flows which comprises an internal conduit for the flow of the first fuel flow, an external annular gorge for the flow of the second fuel flow and at least one orifice for the passage of the second flow which is in fluidic communication with the annular gorge, and in that said at least one orifice and said internal conduit are coaxial and open respectively upstream of the supply pump. ### Claim 2 (depends on 1) The circuit according to claim 1, wherein the device is mounted in a housing arranged upstream of the supply pump, and in which said at least one orifice and said internal conduit open into a mixing area of the housing. ### Claim 3 (depends on 1) The circuit according to claim 1, wherein the supply channel opens downstream into the internal conduit for the flow of the distribution device and the recirculation channel opens into the annular gorge of the distribution device. ### Claim 4 (depends on 2) The circuit according to claim 2, wherein the supply and recirculation channels are configured to open in a secant manner into the housing, wherein a downstream end of the supply channel opens into the internal conduit and an upstream end of the recirculation channel opens into the external annular gorge. ### Claim 5 (depends on 4) The circuit according to claim 4, wherein the downstream end of the supply channel opening into the internal conduit for the flow extends substantially axially or inclined with respect to the axis. ### Claim 6 (depends on 4) The circuit according to claim 4, wherein the upstream end of the recirculation channel opening into the annular gorge extends substantially perpendicularly or inclined with respect to the axis. ### Claim 7 (depends on 1) The circuit according to claim 1, wherein the distribution device comprises a main body of revolution extending about a longitudinal axis and comprising: the internal conduit for the flow of the first fuel flow which extends through the main body along the axis, and a first annular portion configured to form an outlet passage for a second fuel flow, and the first annular portion comprising said at least one orifice for the passage of the second fuel flow which is distributed in an annular row of orifices around the axis. ### Claim 8 (depends on 7) The circuit of claim 7, wherein each orifice extends along an axis parallel to the axis of the internal conduit. ### Claim 9 (depends on 1) The circuit according to claim 1, wherein said internal conduit for the flow and said at least one orifice are configured to open in a transversal manner to an axis about which the supply pump extends. ### Claim 10 (depends on 7) The circuit according to claim 7, wherein the main body further comprises a second annular portion configured to form an inlet passage for the first fuel flow through the internal conduit, the second portion is connected to the first portion via an intermediate portion delimiting at least partly the central opening. ### Claim 11 (depends on 10) The circuit of claim 10, wherein the second portion further comprises at least one annular sealing and attaching groove configured for mounting a sealing element. ### Claim 12 (depends on 1) The circuit according to claim 1, wherein the supply pump is a low pressure pump, e.g., of the rotodynamic type, and/or a high pressure pump, e.g., of the volumetric gear type. ### Claim 13 (depends on 12) The circuit according to claim 12, wherein the housing and the mixing area are arranged upstream of the high pressure pump. ### Claim 14 (depends on 1) The circuit according to claim 1, wherein the internal conduit for the flow of the first fuel flow is formed by a central opening. ### Claim 15 (depends on 1) An aircraft turbomachine, comprising a fuel supply circuit according to claim 1, for a combustion chamber of the turbomachine.