Gas turbine engine with a defined fan axis angle between a fan tip axis and a centerline
An aircraft turbofan gas turbine engine includes a fan assembly, a compressor module, and a turbine module. An electric machine is positioned downstream of the fan assembly and is connected to the turbine module. The fan assembly includes a highest pressure fan stage having a plurality of fan blades...
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| creator | Corin, Robert J Sellers, Benjamin J Hunsley, Richard J Bradbrook, Stephen J |
| description | An aircraft turbofan gas turbine engine includes a fan assembly, a compressor module, and a turbine module. An electric machine is positioned downstream of the fan assembly and is connected to the turbine module. The fan assembly includes a highest pressure fan stage having a plurality of fan blades defining a fan diameter. The turbine module includes a lowest pressure turbine stage having a row of rotor blades. The gas turbine engine has a fan tip axis that joins a radially outer tip of the leading edge of one of the plurality of fan blades of the highest pressure fan stage, and the radially outer tip of the trailing edge of one of the rotor blades of the lowest pressure turbine stage. The fan tip axis lies in a longitudinal plane which contains a centreline of the gas turbine engine. The fan axis angle is between 11 and 20 degrees. |
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An electric machine is positioned downstream of the fan assembly and is connected to the turbine module. The fan assembly includes a highest pressure fan stage having a plurality of fan blades defining a fan diameter. The turbine module includes a lowest pressure turbine stage having a row of rotor blades. The gas turbine engine has a fan tip axis that joins a radially outer tip of the leading edge of one of the plurality of fan blades of the highest pressure fan stage, and the radially outer tip of the trailing edge of one of the rotor blades of the lowest pressure turbine stage. The fan tip axis lies in a longitudinal plane which contains a centreline of the gas turbine engine. 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An electric machine is positioned downstream of the fan assembly and is connected to the turbine module. The fan assembly includes a highest pressure fan stage having a plurality of fan blades defining a fan diameter. The turbine module includes a lowest pressure turbine stage having a row of rotor blades. The gas turbine engine has a fan tip axis that joins a radially outer tip of the leading edge of one of the plurality of fan blades of the highest pressure fan stage, and the radially outer tip of the trailing edge of one of the rotor blades of the lowest pressure turbine stage. The fan tip axis lies in a longitudinal plane which contains a centreline of the gas turbine engine. The fan axis angle is between 11 and 20 degrees.</description><subject>BLASTING</subject><subject>COMBUSTION ENGINES</subject><subject>ENGINE PLANTS IN GENERAL</subject><subject>HEATING</subject><subject>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</subject><subject>JET-PROPULSION PLANTS</subject><subject>LIGHTING</subject><subject>MACHINES OR ENGINES IN GENERAL</subject><subject>MECHANICAL ENGINEERING</subject><subject>NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES</subject><subject>STEAM ENGINES</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2024</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZIhwTyxWKCktSsrMS1VIzUsHUeWZJRkKiQopqWlAXopCWmKeQmJFZrFCYl56TqpCUmpJeWoqUAgsUZJZAJNMAQolp-aVpBblAPXxMLCmJeYUp_JCaW4GRTfXEGcP3dSC_PjU4oJEoNLUkvjQYENDSyMDUxMDJyNjYtQAAOwaOQU</recordid><startdate>20240305</startdate><enddate>20240305</enddate><creator>Corin, Robert J</creator><creator>Sellers, Benjamin J</creator><creator>Hunsley, Richard J</creator><creator>Bradbrook, Stephen J</creator><scope>EVB</scope></search><sort><creationdate>20240305</creationdate><title>Gas turbine engine with a defined fan axis angle between a fan tip axis and a centerline</title><author>Corin, Robert J ; Sellers, Benjamin J ; Hunsley, Richard J ; Bradbrook, Stephen J</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US11920540B23</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2024</creationdate><topic>BLASTING</topic><topic>COMBUSTION ENGINES</topic><topic>ENGINE PLANTS IN GENERAL</topic><topic>HEATING</topic><topic>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</topic><topic>JET-PROPULSION PLANTS</topic><topic>LIGHTING</topic><topic>MACHINES OR ENGINES IN GENERAL</topic><topic>MECHANICAL ENGINEERING</topic><topic>NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES</topic><topic>STEAM ENGINES</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>Corin, Robert J</creatorcontrib><creatorcontrib>Sellers, Benjamin J</creatorcontrib><creatorcontrib>Hunsley, Richard J</creatorcontrib><creatorcontrib>Bradbrook, Stephen J</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Corin, Robert J</au><au>Sellers, Benjamin J</au><au>Hunsley, Richard J</au><au>Bradbrook, Stephen J</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Gas turbine engine with a defined fan axis angle between a fan tip axis and a centerline</title><date>2024-03-05</date><risdate>2024</risdate><abstract>An aircraft turbofan gas turbine engine includes a fan assembly, a compressor module, and a turbine module. An electric machine is positioned downstream of the fan assembly and is connected to the turbine module. The fan assembly includes a highest pressure fan stage having a plurality of fan blades defining a fan diameter. The turbine module includes a lowest pressure turbine stage having a row of rotor blades. The gas turbine engine has a fan tip axis that joins a radially outer tip of the leading edge of one of the plurality of fan blades of the highest pressure fan stage, and the radially outer tip of the trailing edge of one of the rotor blades of the lowest pressure turbine stage. The fan tip axis lies in a longitudinal plane which contains a centreline of the gas turbine engine. The fan axis angle is between 11 and 20 degrees.</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | BLASTING COMBUSTION ENGINES ENGINE PLANTS IN GENERAL HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS |
| title | Gas turbine engine with a defined fan axis angle between a fan tip axis and a centerline |
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