MEANS AND METHOD FOR REDUCING DIFFERENTIAL PRESSURE LOADING IN AN AUGMENTED GAS TURBINE ENGINE
Means and method are disclosed for reducing buckling loads across an afterburner combustion liner in an augmented gas turbine engine. Means for accelerating bypass cooling airflow and then decelerating the accelerated bypass airflow for creating pressure losses to provide reduced-pressure bypass air...
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| creator | MAYER JEFFREY C |
| description | Means and method are disclosed for reducing buckling loads across an afterburner combustion liner in an augmented gas turbine engine. Means for accelerating bypass cooling airflow and then decelerating the accelerated bypass airflow for creating pressure losses to provide reduced-pressure bypass airflow to a plenum surrounding the afterburner liner are disclosed. In a preferred embodiment, the bypass airflow is accelerated to a velocity greater than Mach 1 and is then decelerated to a velocity less than Mach 1 for incurring shock waves for generating pressure losses for reducing differential pressure acting across the liner. |
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Means for accelerating bypass cooling airflow and then decelerating the accelerated bypass airflow for creating pressure losses to provide reduced-pressure bypass airflow to a plenum surrounding the afterburner liner are disclosed. In a preferred embodiment, the bypass airflow is accelerated to a velocity greater than Mach 1 and is then decelerated to a velocity less than Mach 1 for incurring shock waves for generating pressure losses for reducing differential pressure acting across the liner.</description><language>eng</language><subject>BLASTING ; COMBUSTION APPARATUS ; COMBUSTION ENGINES ; COMBUSTION PROCESSES ; GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS ; HEATING ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; JET-PROPULSION PLANTS ; LIGHTING ; MECHANICAL ENGINEERING ; WEAPONS</subject><creationdate>1991</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=19911210&DB=EPODOC&CC=US&NR=5070690A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,777,882,25545,76296</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=19911210&DB=EPODOC&CC=US&NR=5070690A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>MAYER; JEFFREY C</creatorcontrib><title>MEANS AND METHOD FOR REDUCING DIFFERENTIAL PRESSURE LOADING IN AN AUGMENTED GAS TURBINE ENGINE</title><description>Means and method are disclosed for reducing buckling loads across an afterburner combustion liner in an augmented gas turbine engine. Means for accelerating bypass cooling airflow and then decelerating the accelerated bypass airflow for creating pressure losses to provide reduced-pressure bypass airflow to a plenum surrounding the afterburner liner are disclosed. In a preferred embodiment, the bypass airflow is accelerated to a velocity greater than Mach 1 and is then decelerated to a velocity less than Mach 1 for incurring shock waves for generating pressure losses for reducing differential pressure acting across the liner.</description><subject>BLASTING</subject><subject>COMBUSTION APPARATUS</subject><subject>COMBUSTION ENGINES</subject><subject>COMBUSTION PROCESSES</subject><subject>GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS</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>1991</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNqFi7sKAjEQANNYiPoN7g8IAVGxXC-bXOCykTzaOw6JlejB-f8Ywd5qiplZit4RcgRkBY5S6xVoHyCQyo1lA8pqTYE4WezgGijGHAg6j-prLdcRMBtXC1JgMELK4WKZgNhUrMXiPj7msvlxJbaaUtPuyvQayjyNt_Is7yHHgzzJ41ni_n_xASLDMdM</recordid><startdate>19911210</startdate><enddate>19911210</enddate><creator>MAYER; JEFFREY C</creator><scope>EVB</scope></search><sort><creationdate>19911210</creationdate><title>MEANS AND METHOD FOR REDUCING DIFFERENTIAL PRESSURE LOADING IN AN AUGMENTED GAS TURBINE ENGINE</title><author>MAYER; JEFFREY C</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US5070690A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>1991</creationdate><topic>BLASTING</topic><topic>COMBUSTION APPARATUS</topic><topic>COMBUSTION ENGINES</topic><topic>COMBUSTION PROCESSES</topic><topic>GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS</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>MAYER; JEFFREY C</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>MAYER; JEFFREY C</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>MEANS AND METHOD FOR REDUCING DIFFERENTIAL PRESSURE LOADING IN AN AUGMENTED GAS TURBINE ENGINE</title><date>1991-12-10</date><risdate>1991</risdate><abstract>Means and method are disclosed for reducing buckling loads across an afterburner combustion liner in an augmented gas turbine engine. Means for accelerating bypass cooling airflow and then decelerating the accelerated bypass airflow for creating pressure losses to provide reduced-pressure bypass airflow to a plenum surrounding the afterburner liner are disclosed. In a preferred embodiment, the bypass airflow is accelerated to a velocity greater than Mach 1 and is then decelerated to a velocity less than Mach 1 for incurring shock waves for generating pressure losses for reducing differential pressure acting across the liner.</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | BLASTING COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS |
| title | MEANS AND METHOD FOR REDUCING DIFFERENTIAL PRESSURE LOADING IN AN AUGMENTED GAS TURBINE ENGINE |
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