PRESSURE CONTROL FOR BIFURCATED FLOW OF A TURBINE ENGINE

An aircraft propulsion system (20) includes a turbine engine (22) having a propulsor rotor (60), an engine core (42) and a heat exchanger (86). The propulsor rotor (60) is configured to rotate about an axis (24) and direct a first air stream along a primary flowpath (44) that bypasses the engine cor...

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Hauptverfasser:	TERWILLIGER, Neil J, EVANS, Simon W
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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creator	TERWILLIGER, Neil J EVANS, Simon W
description	An aircraft propulsion system (20) includes a turbine engine (22) having a propulsor rotor (60), an engine core (42) and a heat exchanger (86). The propulsor rotor (60) is configured to rotate about an axis (24) and direct a first air stream along a primary flowpath (44) that bypasses the engine core (42) and direct a second air stream along a secondary flowpath (46) with a geometry extending at least eighty degrees about the axis (24). The turbine engine (22) is configured such that the first air stream enters the primary flowpath (44) at a first pressure and the second air stream enters the secondary flowpath (46) at a second pressure that is different than the first pressure. The engine core (42) is configured to drive rotation of the propulsor rotor (60). The heat exchanger (86) is disposed within the secondary flowpath (46).
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The propulsor rotor (60) is configured to rotate about an axis (24) and direct a first air stream along a primary flowpath (44) that bypasses the engine core (42) and direct a second air stream along a secondary flowpath (46) with a geometry extending at least eighty degrees about the axis (24). The turbine engine (22) is configured such that the first air stream enters the primary flowpath (44) at a first pressure and the second air stream enters the secondary flowpath (46) at a second pressure that is different than the first pressure. The engine core (42) is configured to drive rotation of the propulsor rotor (60). 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The propulsor rotor (60) is configured to rotate about an axis (24) and direct a first air stream along a primary flowpath (44) that bypasses the engine core (42) and direct a second air stream along a secondary flowpath (46) with a geometry extending at least eighty degrees about the axis (24). The turbine engine (22) is configured such that the first air stream enters the primary flowpath (44) at a first pressure and the second air stream enters the secondary flowpath (46) at a second pressure that is different than the first pressure. The engine core (42) is configured to drive rotation of the propulsor rotor (60). The heat exchanger (86) is disposed within the secondary flowpath (46).</description><subject>AIR INTAKES FOR JET-PROPULSION PLANTS</subject><subject>BLASTING</subject><subject>COMBUSTION ENGINES</subject><subject>CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS</subject><subject>GAS-TURBINE PLANTS</subject><subject>HEATING</subject><subject>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</subject><subject>JET-PROPULSION PLANTS</subject><subject>LIGHTING</subject><subject>MECHANICAL ENGINEERING</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2024</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZLAICHINDg4NclVw9vcLCfL3UXDzD1Jw8nQLDXJ2DHF1UXDz8Q9X8HdTcFQICQ1y8vRzVXD1cwdSPAysaYk5xam8UJqbQcHNNcTZQze1ID8-tbggMTk1L7Uk3jXAxMTMxMLC0NHQmAglABLdKAQ</recordid><startdate>20241120</startdate><enddate>20241120</enddate><creator>TERWILLIGER, Neil J</creator><creator>EVANS, Simon W</creator><scope>EVB</scope></search><sort><creationdate>20241120</creationdate><title>PRESSURE CONTROL FOR BIFURCATED FLOW OF A TURBINE ENGINE</title><author>TERWILLIGER, Neil J ; EVANS, Simon W</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_EP4464881A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; fre ; ger</language><creationdate>2024</creationdate><topic>AIR INTAKES FOR JET-PROPULSION PLANTS</topic><topic>BLASTING</topic><topic>COMBUSTION ENGINES</topic><topic>CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS</topic><topic>GAS-TURBINE PLANTS</topic><topic>HEATING</topic><topic>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</topic><topic>JET-PROPULSION PLANTS</topic><topic>LIGHTING</topic><topic>MECHANICAL ENGINEERING</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>TERWILLIGER, Neil J</creatorcontrib><creatorcontrib>EVANS, Simon W</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>TERWILLIGER, Neil J</au><au>EVANS, Simon W</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>PRESSURE CONTROL FOR BIFURCATED FLOW OF A TURBINE ENGINE</title><date>2024-11-20</date><risdate>2024</risdate><abstract>An aircraft propulsion system (20) includes a turbine engine (22) having a propulsor rotor (60), an engine core (42) and a heat exchanger (86). The propulsor rotor (60) is configured to rotate about an axis (24) and direct a first air stream along a primary flowpath (44) that bypasses the engine core (42) and direct a second air stream along a secondary flowpath (46) with a geometry extending at least eighty degrees about the axis (24). The turbine engine (22) is configured such that the first air stream enters the primary flowpath (44) at a first pressure and the second air stream enters the secondary flowpath (46) at a second pressure that is different than the first pressure. The engine core (42) is configured to drive rotation of the propulsor rotor (60). The heat exchanger (86) is disposed within the secondary flowpath (46).</abstract><oa>free_for_read</oa></addata></record>
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language	eng ; fre ; ger
recordid	cdi_epo_espacenet_EP4464881A1
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subjects	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
title	PRESSURE CONTROL FOR BIFURCATED FLOW OF A TURBINE ENGINE
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