INLET PERFORMANCE MEASUREMENT SYSTEM FOR GAS TURBINE ENGINE
A performance measurement system (56) of an inlet of a gas turbine engine includes a probe strut (58) configured for installation to a case strut (52) of an inlet case (46) of a gas turbine engine. The probe strut (58) includes one or more probes (64) extending therefrom configured to measure one or...
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| creator | HENDRICKS, Richard C RICE, William W COVINO, Alfred F THOMESEN, Douglas H HACKETT, Bryan J |
| description | A performance measurement system (56) of an inlet of a gas turbine engine includes a probe strut (58) configured for installation to a case strut (52) of an inlet case (46) of a gas turbine engine. The probe strut (58) includes one or more probes (64) extending therefrom configured to measure one or more characteristics of an airflow past the one or more probes (64), a first attachment point configured to secure the probe strut (58) to a hub portion (48) of the inlet case (46), and a second attachment point configured to secure the probe strut (58) to an outer case portion (50) of the inlet case (46). A data acquisition module (92) is located at a central longitudinal axis of the inlet and is operably connected to the probe (64) to collect sensed data therefrom. The probe strut (58) and the data acquisition module (92) are configured to be installed, removed, and/or relocated without removal of the inlet case from the gas turbine engine. |
| format | Patent |
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The probe strut (58) includes one or more probes (64) extending therefrom configured to measure one or more characteristics of an airflow past the one or more probes (64), a first attachment point configured to secure the probe strut (58) to a hub portion (48) of the inlet case (46), and a second attachment point configured to secure the probe strut (58) to an outer case portion (50) of the inlet case (46). A data acquisition module (92) is located at a central longitudinal axis of the inlet and is operably connected to the probe (64) to collect sensed data therefrom. The probe strut (58) and the data acquisition module (92) are configured to be installed, removed, and/or relocated without removal of the inlet case from the gas turbine engine.</description><language>eng ; fre ; ger</language><subject>AIR INTAKES FOR JET-PROPULSION PLANTS ; BLASTING ; COMBUSTION ENGINES ; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ; ENGINE PLANTS IN GENERAL ; GAS-TURBINE PLANTS ; HEATING ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; LIGHTING ; MACHINES OR ENGINES IN GENERAL ; MEASURING ; MECHANICAL ENGINEERING ; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES ; PHYSICS ; STEAM ENGINES ; TESTING ; TESTING STATIC OR DYNAMIC BALANCE OF MACHINES ORSTRUCTURES ; TESTING STRUCTURES OR APPARATUS NOT OTHERWISE PROVIDED FOR ; WEAPONS</subject><creationdate>2020</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=20201007&DB=EPODOC&CC=EP&NR=3473817B1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20201007&DB=EPODOC&CC=EP&NR=3473817B1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>HENDRICKS, Richard C</creatorcontrib><creatorcontrib>RICE, William W</creatorcontrib><creatorcontrib>COVINO, Alfred F</creatorcontrib><creatorcontrib>THOMESEN, Douglas H</creatorcontrib><creatorcontrib>HACKETT, Bryan J</creatorcontrib><title>INLET PERFORMANCE MEASUREMENT SYSTEM FOR GAS TURBINE ENGINE</title><description>A performance measurement system (56) of an inlet of a gas turbine engine includes a probe strut (58) configured for installation to a case strut (52) of an inlet case (46) of a gas turbine engine. The probe strut (58) includes one or more probes (64) extending therefrom configured to measure one or more characteristics of an airflow past the one or more probes (64), a first attachment point configured to secure the probe strut (58) to a hub portion (48) of the inlet case (46), and a second attachment point configured to secure the probe strut (58) to an outer case portion (50) of the inlet case (46). A data acquisition module (92) is located at a central longitudinal axis of the inlet and is operably connected to the probe (64) to collect sensed data therefrom. The probe strut (58) and the data acquisition module (92) are configured to be installed, removed, and/or relocated without removal of the inlet case from the gas turbine engine.</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>ENGINE PLANTS IN GENERAL</subject><subject>GAS-TURBINE PLANTS</subject><subject>HEATING</subject><subject>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</subject><subject>LIGHTING</subject><subject>MACHINES OR ENGINES IN GENERAL</subject><subject>MEASURING</subject><subject>MECHANICAL ENGINEERING</subject><subject>NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES</subject><subject>PHYSICS</subject><subject>STEAM ENGINES</subject><subject>TESTING</subject><subject>TESTING STATIC OR DYNAMIC BALANCE OF MACHINES ORSTRUCTURES</subject><subject>TESTING STRUCTURES OR APPARATUS NOT OTHERWISE PROVIDED FOR</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2020</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZLD29PNxDVEIcA1y8w_ydfRzdlXwdXUMDg1y9XX1C1EIjgwOcfVVAMopuDsGK4SEBjl5-rkquPq5AykeBta0xJziVF4ozc2g4OYa4uyhm1qQH59aXJCYnJqXWhLvGmBsYm5sYWjuZGhMhBIApC4pGA</recordid><startdate>20201007</startdate><enddate>20201007</enddate><creator>HENDRICKS, Richard C</creator><creator>RICE, William W</creator><creator>COVINO, Alfred F</creator><creator>THOMESEN, Douglas H</creator><creator>HACKETT, Bryan J</creator><scope>EVB</scope></search><sort><creationdate>20201007</creationdate><title>INLET PERFORMANCE MEASUREMENT SYSTEM FOR GAS TURBINE ENGINE</title><author>HENDRICKS, Richard C ; RICE, William W ; COVINO, Alfred F ; THOMESEN, Douglas H ; HACKETT, Bryan J</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_EP3473817B13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; fre ; ger</language><creationdate>2020</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>ENGINE PLANTS IN GENERAL</topic><topic>GAS-TURBINE PLANTS</topic><topic>HEATING</topic><topic>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</topic><topic>LIGHTING</topic><topic>MACHINES OR ENGINES IN GENERAL</topic><topic>MEASURING</topic><topic>MECHANICAL ENGINEERING</topic><topic>NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES</topic><topic>PHYSICS</topic><topic>STEAM ENGINES</topic><topic>TESTING</topic><topic>TESTING STATIC OR DYNAMIC BALANCE OF MACHINES ORSTRUCTURES</topic><topic>TESTING STRUCTURES OR APPARATUS NOT OTHERWISE PROVIDED FOR</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>HENDRICKS, Richard C</creatorcontrib><creatorcontrib>RICE, William W</creatorcontrib><creatorcontrib>COVINO, Alfred F</creatorcontrib><creatorcontrib>THOMESEN, Douglas H</creatorcontrib><creatorcontrib>HACKETT, Bryan J</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>HENDRICKS, Richard C</au><au>RICE, William W</au><au>COVINO, Alfred F</au><au>THOMESEN, Douglas H</au><au>HACKETT, Bryan J</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>INLET PERFORMANCE MEASUREMENT SYSTEM FOR GAS TURBINE ENGINE</title><date>2020-10-07</date><risdate>2020</risdate><abstract>A performance measurement system (56) of an inlet of a gas turbine engine includes a probe strut (58) configured for installation to a case strut (52) of an inlet case (46) of a gas turbine engine. The probe strut (58) includes one or more probes (64) extending therefrom configured to measure one or more characteristics of an airflow past the one or more probes (64), a first attachment point configured to secure the probe strut (58) to a hub portion (48) of the inlet case (46), and a second attachment point configured to secure the probe strut (58) to an outer case portion (50) of the inlet case (46). A data acquisition module (92) is located at a central longitudinal axis of the inlet and is operably connected to the probe (64) to collect sensed data therefrom. The probe strut (58) and the data acquisition module (92) are configured to be installed, removed, and/or relocated without removal of the inlet case from the gas turbine engine.</abstract><oa>free_for_read</oa></addata></record> |
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| language | eng ; fre ; ger |
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| subjects | AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MEASURING MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PHYSICS STEAM ENGINES TESTING TESTING STATIC OR DYNAMIC BALANCE OF MACHINES ORSTRUCTURES TESTING STRUCTURES OR APPARATUS NOT OTHERWISE PROVIDED FOR WEAPONS |
| title | INLET PERFORMANCE MEASUREMENT SYSTEM FOR GAS TURBINE ENGINE |
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