AIRCRAFT HEAT MANAGEMENT
A gas turbine engine includes an engine core with a combustor; a turbine including turbine blades; a compressor as a source of cooling air for the turbine blades; and an inducer to accelerate and direct the cooling air onto the turbine blades, and a modulating valve to allow or block cooling air flo...
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| creator | BEMMENT, Craig W MINELLI, Andrea KEELER, Benjamin J YATES, Martin K MADDEN, Christopher P SWANN, Peter |
| description | A gas turbine engine includes an engine core with a combustor; a turbine including turbine blades; a compressor as a source of cooling air for the turbine blades; and an inducer to accelerate and direct the cooling air onto the turbine blades, and a modulating valve to allow or block cooling air flow into a subset of airflow passageways of the inducer; and a fuel management system to provide fuel to the combustor. The fuel management system includes a primary fuel-oil heat exchanger and a secondary fuel-oil heat exchanger through which oil and the fuel flow, to transfer heat between the oil and the fuel. A method of operating the engine includes using the modulating valve to adjust the cooling air flow based on turbine inlet temperature; and transferring 200-600 kJ/m3 of heat to the fuel from the oil in the primary fuel-oil heat exchanger at cruise conditions. |
| format | Patent |
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The fuel management system includes a primary fuel-oil heat exchanger and a secondary fuel-oil heat exchanger through which oil and the fuel flow, to transfer heat between the oil and the fuel. A method of operating the engine includes using the modulating valve to adjust the cooling air flow based on turbine inlet temperature; and transferring 200-600 kJ/m3 of heat to the fuel from the oil in the primary fuel-oil heat exchanger at cruise conditions.</description><language>eng</language><subject>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 ; LIGHTING ; MECHANICAL ENGINEERING ; WEAPONS</subject><creationdate>2024</creationdate><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><linktohtml>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20240815&DB=EPODOC&CC=US&NR=2024271566A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25555,76308</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20240815&DB=EPODOC&CC=US&NR=2024271566A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>BEMMENT, Craig W</creatorcontrib><creatorcontrib>MINELLI, Andrea</creatorcontrib><creatorcontrib>KEELER, Benjamin J</creatorcontrib><creatorcontrib>YATES, Martin K</creatorcontrib><creatorcontrib>MADDEN, Christopher P</creatorcontrib><creatorcontrib>SWANN, Peter</creatorcontrib><title>AIRCRAFT HEAT MANAGEMENT</title><description>A gas turbine engine includes an engine core with a combustor; a turbine including turbine blades; a compressor as a source of cooling air for the turbine blades; and an inducer to accelerate and direct the cooling air onto the turbine blades, and a modulating valve to allow or block cooling air flow into a subset of airflow passageways of the inducer; and a fuel management system to provide fuel to the combustor. The fuel management system includes a primary fuel-oil heat exchanger and a secondary fuel-oil heat exchanger through which oil and the fuel flow, to transfer heat between the oil and the fuel. A method of operating the engine includes using the modulating valve to adjust the cooling air flow based on turbine inlet temperature; and transferring 200-600 kJ/m3 of heat to the fuel from the oil in the primary fuel-oil heat exchanger at cruise conditions.</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>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>eNrjZJBw9AxyDnJ0C1HwcHUMUfB19HN0d_V19QvhYWBNS8wpTuWF0twMym6uIc4euqkF-fGpxQWJyal5qSXxocFGBkYmRuaGpmZmjobGxKkCAGM3IIQ</recordid><startdate>20240815</startdate><enddate>20240815</enddate><creator>BEMMENT, Craig W</creator><creator>MINELLI, Andrea</creator><creator>KEELER, Benjamin J</creator><creator>YATES, Martin K</creator><creator>MADDEN, Christopher P</creator><creator>SWANN, Peter</creator><scope>EVB</scope></search><sort><creationdate>20240815</creationdate><title>AIRCRAFT HEAT MANAGEMENT</title><author>BEMMENT, Craig W ; MINELLI, Andrea ; KEELER, Benjamin J ; YATES, Martin K ; MADDEN, Christopher P ; SWANN, Peter</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US2024271566A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</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>LIGHTING</topic><topic>MECHANICAL ENGINEERING</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>BEMMENT, Craig W</creatorcontrib><creatorcontrib>MINELLI, Andrea</creatorcontrib><creatorcontrib>KEELER, Benjamin J</creatorcontrib><creatorcontrib>YATES, Martin K</creatorcontrib><creatorcontrib>MADDEN, Christopher P</creatorcontrib><creatorcontrib>SWANN, Peter</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>BEMMENT, Craig W</au><au>MINELLI, Andrea</au><au>KEELER, Benjamin J</au><au>YATES, Martin K</au><au>MADDEN, Christopher P</au><au>SWANN, Peter</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>AIRCRAFT HEAT MANAGEMENT</title><date>2024-08-15</date><risdate>2024</risdate><abstract>A gas turbine engine includes an engine core with a combustor; a turbine including turbine blades; a compressor as a source of cooling air for the turbine blades; and an inducer to accelerate and direct the cooling air onto the turbine blades, and a modulating valve to allow or block cooling air flow into a subset of airflow passageways of the inducer; and a fuel management system to provide fuel to the combustor. The fuel management system includes a primary fuel-oil heat exchanger and a secondary fuel-oil heat exchanger through which oil and the fuel flow, to transfer heat between the oil and the fuel. A method of operating the engine includes using the modulating valve to adjust the cooling air flow based on turbine inlet temperature; and transferring 200-600 kJ/m3 of heat to the fuel from the oil in the primary fuel-oil heat exchanger at cruise conditions.</abstract><oa>free_for_read</oa></addata></record> |
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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 LIGHTING MECHANICAL ENGINEERING WEAPONS |
| title | AIRCRAFT HEAT MANAGEMENT |
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