GAS TURBINE ENGINE BLADE, CORRESPONDING GAS TURBINE ENGINE AND METHOD FOR A GAS TURBINE ENGINE BLADE

GAS TURBINE ENGINE BLADE, CORRESPONDING GAS TURBINE ENGINE AND METHOD FOR A GAS TURBINE ENGINE BLADE

A gas turbine engine (20) blade (64) includes a platform (68) that has an inner side (68A) and an outer side (68B), a root (70) that extends outwardly from the inner side (68A), and an airfoil (72) that extends outwardly from a base (72A) at the outer side (68B) to a tip end (72B). The airfoil (72)...

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Hauptverfasser: NIEZELSKI, David A, AUXIER, James Tilsley, JENNINGS, Timothy J
Format: Patent
Sprache:eng ; fre ; ger
Schlagworte:
BLASTING
ENGINE PLANTS IN GENERAL
HEATING
LIGHTING
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
STEAM ENGINES
WEAPONS
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creator NIEZELSKI, David A
AUXIER, James Tilsley
JENNINGS, Timothy J
description A gas turbine engine (20) blade (64) includes a platform (68) that has an inner side (68A) and an outer side (68B), a root (70) that extends outwardly from the inner side (68A), and an airfoil (72) that extends outwardly from a base (72A) at the outer side (68B) to a tip end (72B). The airfoil (72) includes a leading edge and a trailing edge and a first side wall (72C) and a second side wall (72D). The first side wall (72C) and the second side wall (72D) join the leading edge and the trailing edge and at least partially define one or more cavities (74) in the airfoil (72). The airfoil (72) has a span from the base (72A) to the tip end (72B), with the base (72A) being at 0% of the span and the tip end (72B) being at 100% of the span. The first side wall (72C) includes an axial row (76) of cooling holes (78) at 90% or greater of the span.
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The airfoil (72) includes a leading edge and a trailing edge and a first side wall (72C) and a second side wall (72D). The first side wall (72C) and the second side wall (72D) join the leading edge and the trailing edge and at least partially define one or more cavities (74) in the airfoil (72). The airfoil (72) has a span from the base (72A) to the tip end (72B), with the base (72A) being at 0% of the span and the tip end (72B) being at 100% of the span. The first side wall (72C) includes an axial row (76) of cooling holes (78) at 90% or greater of the span.</description><language>eng ; fre ; ger</language><subject>BLASTING ; ENGINE PLANTS IN GENERAL ; HEATING ; LIGHTING ; MACHINES OR ENGINES IN GENERAL ; MECHANICAL ENGINEERING ; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES ; STEAM ENGINES ; WEAPONS</subject><creationdate>2018</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&amp;date=20180321&amp;DB=EPODOC&amp;CC=EP&amp;NR=3296511A2$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&amp;date=20180321&amp;DB=EPODOC&amp;CC=EP&amp;NR=3296511A2$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>NIEZELSKI, David A</creatorcontrib><creatorcontrib>AUXIER, James Tilsley</creatorcontrib><creatorcontrib>JENNINGS, Timothy J</creatorcontrib><title>GAS TURBINE ENGINE BLADE, CORRESPONDING GAS TURBINE ENGINE AND METHOD FOR A GAS TURBINE ENGINE BLADE</title><description>A gas turbine engine (20) blade (64) includes a platform (68) that has an inner side (68A) and an outer side (68B), a root (70) that extends outwardly from the inner side (68A), and an airfoil (72) that extends outwardly from a base (72A) at the outer side (68B) to a tip end (72B). 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The first side wall (72C) includes an axial row (76) of cooling holes (78) at 90% or greater of the span.</description><subject>BLASTING</subject><subject>ENGINE PLANTS IN GENERAL</subject><subject>HEATING</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>2018</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZEhxdwxWCAkNcvL0c1Vw9XMHUU4-ji6uOgrO_kFBrsEB_n4unn7uCljUOfq5KPi6hnj4uyi4-QcpOCrgMouHgTUtMac4lRdKczMouLmGOHvophbkx6cWFyQmp-allsS7BhgbWZqZGho6GhkToQQAeiczPg</recordid><startdate>20180321</startdate><enddate>20180321</enddate><creator>NIEZELSKI, David A</creator><creator>AUXIER, James Tilsley</creator><creator>JENNINGS, Timothy J</creator><scope>EVB</scope></search><sort><creationdate>20180321</creationdate><title>GAS TURBINE ENGINE BLADE, CORRESPONDING GAS TURBINE ENGINE AND METHOD FOR A GAS TURBINE ENGINE BLADE</title><author>NIEZELSKI, David A ; AUXIER, James Tilsley ; JENNINGS, Timothy J</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_EP3296511A23</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; fre ; ger</language><creationdate>2018</creationdate><topic>BLASTING</topic><topic>ENGINE PLANTS IN GENERAL</topic><topic>HEATING</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>NIEZELSKI, David A</creatorcontrib><creatorcontrib>AUXIER, James Tilsley</creatorcontrib><creatorcontrib>JENNINGS, Timothy J</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>NIEZELSKI, David A</au><au>AUXIER, James Tilsley</au><au>JENNINGS, Timothy J</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>GAS TURBINE ENGINE BLADE, CORRESPONDING GAS TURBINE ENGINE AND METHOD FOR A GAS TURBINE ENGINE BLADE</title><date>2018-03-21</date><risdate>2018</risdate><abstract>A gas turbine engine (20) blade (64) includes a platform (68) that has an inner side (68A) and an outer side (68B), a root (70) that extends outwardly from the inner side (68A), and an airfoil (72) that extends outwardly from a base (72A) at the outer side (68B) to a tip end (72B). 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subjects BLASTING
ENGINE PLANTS IN GENERAL
HEATING
LIGHTING
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
STEAM ENGINES
WEAPONS
title GAS TURBINE ENGINE BLADE, CORRESPONDING GAS TURBINE ENGINE AND METHOD FOR A GAS TURBINE ENGINE BLADE
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