TURBOFAN ARRANGEMENT WITH BLADE CHANNEL VARIATIONS
A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section having a fan including a rotor hub rotatable about an engine longitudinal axis and an array of fan blades, a geared architecture, a compressor section including a low pressure compresso...
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| creator | Chuang, Sue-Li Gallagher, Edward J |
| description | A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section having a fan including a rotor hub rotatable about an engine longitudinal axis and an array of fan blades, a geared architecture, a compressor section including a low pressure compressor and a high pressure compressor, a turbine section including a low pressure turbine and a high pressure turbine. The low pressure turbine drives the fan through the geared architecture. Each fan blade of the array of fan blades includes pressure and suction sides and extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, and facing pressure and suction sides of adjacent fan blades define a channel in a chordwise direction having a width between the facing pressure and suction sides at a given span position of the adjacent fan blades. The width at each pressure side location along the channel is defined as a minimum distance to a location along the suction side, and the width converges along the channel for at least some span positions. |
| format | Patent |
| fullrecord | <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_US2020102830A1</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>US2020102830A1</sourcerecordid><originalsourceid>FETCH-epo_espacenet_US2020102830A13</originalsourceid><addsrcrecordid>eNrjZDAKCQ1y8ndz9FNwDApy9HN39XX1C1EI9wzxUHDycXRxVXD2cPTzc_VRCHMM8nQM8fT3C-ZhYE1LzClO5YXS3AzKbq4hzh66qQX58anFBYnJqXmpJfGhwUYGRgaGBkYWxgaOhsbEqQIAGA8nsw</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>TURBOFAN ARRANGEMENT WITH BLADE CHANNEL VARIATIONS</title><source>esp@cenet</source><creator>Chuang, Sue-Li ; Gallagher, Edward J</creator><creatorcontrib>Chuang, Sue-Li ; Gallagher, Edward J</creatorcontrib><description>A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section having a fan including a rotor hub rotatable about an engine longitudinal axis and an array of fan blades, a geared architecture, a compressor section including a low pressure compressor and a high pressure compressor, a turbine section including a low pressure turbine and a high pressure turbine. The low pressure turbine drives the fan through the geared architecture. Each fan blade of the array of fan blades includes pressure and suction sides and extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, and facing pressure and suction sides of adjacent fan blades define a channel in a chordwise direction having a width between the facing pressure and suction sides at a given span position of the adjacent fan blades. The width at each pressure side location along the channel is defined as a minimum distance to a location along the suction side, and the width converges along the channel for at least some span positions.</description><language>eng</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 ; MECHANICAL ENGINEERING ; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES ; NON-POSITIVE DISPLACEMENT PUMPS ; POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS ; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS ; STEAM ENGINES ; 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=20200402&DB=EPODOC&CC=US&NR=2020102830A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,778,883,25547,76298</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20200402&DB=EPODOC&CC=US&NR=2020102830A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Chuang, Sue-Li</creatorcontrib><creatorcontrib>Gallagher, Edward J</creatorcontrib><title>TURBOFAN ARRANGEMENT WITH BLADE CHANNEL VARIATIONS</title><description>A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section having a fan including a rotor hub rotatable about an engine longitudinal axis and an array of fan blades, a geared architecture, a compressor section including a low pressure compressor and a high pressure compressor, a turbine section including a low pressure turbine and a high pressure turbine. The low pressure turbine drives the fan through the geared architecture. Each fan blade of the array of fan blades includes pressure and suction sides and extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, and facing pressure and suction sides of adjacent fan blades define a channel in a chordwise direction having a width between the facing pressure and suction sides at a given span position of the adjacent fan blades. The width at each pressure side location along the channel is defined as a minimum distance to a location along the suction side, and the width converges along the channel for at least some span positions.</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>MECHANICAL ENGINEERING</subject><subject>NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES</subject><subject>NON-POSITIVE DISPLACEMENT PUMPS</subject><subject>POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS</subject><subject>PUMPS FOR LIQUIDS OR ELASTIC FLUIDS</subject><subject>STEAM ENGINES</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2020</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZDAKCQ1y8ndz9FNwDApy9HN39XX1C1EI9wzxUHDycXRxVXD2cPTzc_VRCHMM8nQM8fT3C-ZhYE1LzClO5YXS3AzKbq4hzh66qQX58anFBYnJqXmpJfGhwUYGRgaGBkYWxgaOhsbEqQIAGA8nsw</recordid><startdate>20200402</startdate><enddate>20200402</enddate><creator>Chuang, Sue-Li</creator><creator>Gallagher, Edward J</creator><scope>EVB</scope></search><sort><creationdate>20200402</creationdate><title>TURBOFAN ARRANGEMENT WITH BLADE CHANNEL VARIATIONS</title><author>Chuang, Sue-Li ; Gallagher, Edward J</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US2020102830A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</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>MECHANICAL ENGINEERING</topic><topic>NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES</topic><topic>NON-POSITIVE DISPLACEMENT PUMPS</topic><topic>POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS</topic><topic>PUMPS FOR LIQUIDS OR ELASTIC FLUIDS</topic><topic>STEAM ENGINES</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>Chuang, Sue-Li</creatorcontrib><creatorcontrib>Gallagher, Edward J</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Chuang, Sue-Li</au><au>Gallagher, Edward J</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>TURBOFAN ARRANGEMENT WITH BLADE CHANNEL VARIATIONS</title><date>2020-04-02</date><risdate>2020</risdate><abstract>A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section having a fan including a rotor hub rotatable about an engine longitudinal axis and an array of fan blades, a geared architecture, a compressor section including a low pressure compressor and a high pressure compressor, a turbine section including a low pressure turbine and a high pressure turbine. The low pressure turbine drives the fan through the geared architecture. Each fan blade of the array of fan blades includes pressure and suction sides and extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, and facing pressure and suction sides of adjacent fan blades define a channel in a chordwise direction having a width between the facing pressure and suction sides at a given span position of the adjacent fan blades. The width at each pressure side location along the channel is defined as a minimum distance to a location along the suction side, and the width converges along the channel for at least some span positions.</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 ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES NON-POSITIVE DISPLACEMENT PUMPS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS STEAM ENGINES WEAPONS |
| title | TURBOFAN ARRANGEMENT WITH BLADE CHANNEL VARIATIONS |
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