# US 10,371,094 B2 · Nozzle arrangement for a gas turbine engine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,371,094 B2 - Document ID: US10371094B2 - Status: Granted - Kind: B2 - Application number: 14/789,643 - Filed: 2015-07-01 - Published: 2016-01-14 - Granted: 2019-08-06 - Earliest claimed: 2014-07-09 - Assignees: ROLLS-ROYCE plc - Applicants: Rolls-Royce PLC - Inventors: Andrew Martin Rolt - Web page: https://patentgrep.com/patent/US10371094B2 ## CPC - F02K 3/025: {the by-pass flow being at least partly used to create an independent thrust component} - F01D 17/143: {the shiftable member being a wall, or part thereof of a radial diffuser} - F02C 3/04: having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) - F02K 1/08: by axially moving or transversely deforming an internal member, e.g. the exhaust cone - F02K 1/09: by axially moving an external member, e.g. a shroud (F02K1/12 takes precedence) - F02K 1/15: Control or regulation - F02K 1/48: Corrugated nozzles - F02K 3/06: with front fan - F02K 3/075: controlling flow ratio between flows - F05D 2220/323: for aircraft propulsion, e.g. jet engines - F05D 2250/311: the axes being in line - F05D 2250/41: with one degree of freedom - F05D 2260/20: Heat transfer, e.g. cooling - F05D 2260/213: by the provision of a heat exchanger within the cooling circuit - F05D 2260/57: using servos, independent actuators, etc. - F05D 2260/96: Preventing, counteracting or reducing vibration or noise - F05D 2270/101: Compressor surge or stall - 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) - 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 - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A gas turbine engine comprising: a bypass duct having a bypass nozzle; an engine core having a core nozzle; and, a mixer duct defined by a mixer fairing and having a mixer nozzle, wherein the mixer duct is arranged to receive an airflow from the bypass duct through a mixer duct inlet and an airflow from the engine core, when in use, and the geometry of the mixer duct is selectively adjustable by moving the mixer fairing relative to the bypass duct and engine core in use. ## Claims ### Claim 1 A gas turbine engine comprising: a bypass duct having a bypass nozzle; an engine core having a core nozzle; a pylon which is attached to the wing or airframe of an aircraft; a mixer fairing defining a mixer duct having a mixer duct inlet and a mixer nozzle, the mixer fairing is movably mounted to mounting rails on each side of the pylon; and a tail cone, wherein the mixer duct is arranged to receive an airflow from the bypass duct through the mixer duct inlet and an airflow from the engine core, when in use, and a geometry of the mixer duct is selectively adjustable by moving the mixer fairing relative to the bypass duct and engine core in use, the mixer fairing is movable by a first amount between a first mixer fairing position and a second mixer fairing position which simultaneously alters one or more of: an output flow area of the bypass nozzle, an output flow area of the mixer nozzle, and, a throat area of the mixer duct inlet, such that the respective in use airflows are altered, and the tail cone is movable by a second amount, different than the first amount, between a first tail cone position and a second tail cone position. ### Claim 2 (depends on 1) A gas turbine engine as claimed in claim 1, wherein moving the mixer fairing between the first and second mixer fairing position alters all of: the output flow area of the bypass nozzle, the output flow area of the mixer nozzle, and, the throat area of the mixer duct inlet. ### Claim 3 (depends on 1) A gas turbine engine as claimed in claim 1, wherein a portion of radially outer wall of the mixer fairing downstream of a leading edge is substantially parallel to an axis of movement such that moving the mixer fairing between the first and second mixer fairing positions alters the output flow area of the mixer nozzle and moving the mixer fairing between the second mixer fairing position and a third mixer fairing position alters the output flow area of the bypass nozzle and mixer nozzle. ### Claim 4 (depends on 3) A gas turbine engine as claimed in claim 3, wherein moving the mixer fairing between the second and third mixer fairing positions additionally alters the mixer duct inlet flow area. ### Claim 5 (depends on 1) A gas turbine engine as claimed in claim 1, wherein the mixer fairing is axially translatable relative to a principal axis of the gas turbine engine so as to alter the geometry of the mixer duct. ### Claim 6 (depends on 1) A gas turbine engine as claimed in claim 1 wherein the core nozzle exits directly into the mixer duct. ### Claim 7 (depends on 1) A gas turbine engine as claimed in claim 1 wherein a leading edge of the mixer fairing is at least partially located within the bypass duct in the first and second mixer fairing positions. ### Claim 8 (depends on 1) A gas turbine engine as claimed in claim 1 wherein either or both of the mixer fairing and the trailing edge of a core fairing includes lobes to aid mixing of a engine core airflow and bypass airflow. ### Claim 9 (depends on 1) A gas turbine engine as claimed in claim 1 wherein the mixer fairing and tail cone are configured to move simultaneously. ### Claim 10 (depends on 1) A gas turbine engine as claimed in any of claim 1 wherein a portion of the mixer duct is defined by the tail cone and the mixer duct fairing which are arranged to have a chute therebetween, the minimum flow area of which is adjustable with the movement of the mixer fairing. ### Claim 11 (depends on 1) A gas turbine engine as claimed in claim 1, wherein at least a portion of the mixer fairing exchanges heat between a bypass airflow exiting the bypass nozzle and an airflow passing through the mixer duct. ### Claim 12 (depends on 1) A gas turbine engine as claimed in claim 1, further comprising a thrust reverser having at least one door which is operable to substantially block the bypass duct in a thrust reversing operation, wherein the door includes at least one aperture in an upstream flow path relative to a leading edge of the mixer Fairing such that the leading edge of the mixer fairing is provided with a cooling air flow when the thrust reverser door is deployed. ### Claim 13 (depends on 1) A gas turbine engine as claimed in claim 1, further comprising a thrust measurement system and at least one sensor operably connected to the thrust measurement system, wherein the sensor is configured to provide the thrust measurement system with a signal which is representative of the position of the mixer fairing. ### Claim 14 (depends on 13) A gas turbine engine as claimed in claim 13, further comprising a tail cone position sensor. ### Claim 15 (depends on 1) A gas turbine engine as claimed in claim 1, an engine control system and at least one sensor operably connected to the engine control system, wherein the sensor is configured to provide the engine control system with a signal which is representative of the position of the mixer fairing. ### Claim 16 (depends on 15) A gas turbine engine as claimed in claim 15, wherein the engine control system reduces the output flow area of the bypass nozzle and the output flow area of the mixer nozzle with an increase in fan speed of a main propulsive fan of the gas turbine engine. ### Claim 17 (depends on 1) A gas turbine engine as claimed in claim 1, wherein the first amount and the second amount are in an axial direction of the gas turbine engine. ### Claim 18 (depends on 1) A gas turbine engine as claimed in claim 1, wherein the mixer fairing includes a gap that circumferentially splits the mixer fairing at the pylon, and the gas turbine engine further including the mounting rails on each side of the pylon that connect the mixer fairing to the pylon, the mounting rails being configured to allow the mixer fairing to move relative to the pylon.