Turbine blade with enhanced cooling and profile optimization
A first-stage turbine blade includes an airfoil having a profile according to Table I. The airfoil has a plurality of cooling air passages extending linearly from the root portion to the tip portion of the airfoil. The blade includes a shank having a pair of cavities in communication through the bla...
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| creator | GREGORY BRENT A BARRY VINCENT ANTHONY ABUAF NESIM |
| description | A first-stage turbine blade includes an airfoil having a profile according to Table I. The airfoil has a plurality of cooling air passages extending linearly from the root portion to the tip portion of the airfoil. The blade includes a shank having a pair of cavities in communication through the blade dovetail with a plenum in the wheel space for supplying cooling air to the passages in the airfoil. The cooling passages in the airfoil terminate in a recess at the tip portion which has an opening adjacent the trailing edge of the airfoil and along the suction side to enable egress of cooling air into the hot gas stream on the low pressure side of the airfoil. The majority of the cooling passages are turbulated. Certain of those passages are arranged in rows lying adjacent to the pressure and suction sides of the airfoil. |
| format | Patent |
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The airfoil has a plurality of cooling air passages extending linearly from the root portion to the tip portion of the airfoil. The blade includes a shank having a pair of cavities in communication through the blade dovetail with a plenum in the wheel space for supplying cooling air to the passages in the airfoil. The cooling passages in the airfoil terminate in a recess at the tip portion which has an opening adjacent the trailing edge of the airfoil and along the suction side to enable egress of cooling air into the hot gas stream on the low pressure side of the airfoil. The majority of the cooling passages are turbulated. Certain of those passages are arranged in rows lying adjacent to the pressure and suction sides of the airfoil.</description><edition>6</edition><language>eng</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>1999</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=19991109&DB=EPODOC&CC=US&NR=5980209A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25543,76293</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=19991109&DB=EPODOC&CC=US&NR=5980209A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>GREGORY; BRENT A</creatorcontrib><creatorcontrib>BARRY; VINCENT ANTHONY</creatorcontrib><creatorcontrib>ABUAF; NESIM</creatorcontrib><title>Turbine blade with enhanced cooling and profile optimization</title><description>A first-stage turbine blade includes an airfoil having a profile according to Table I. The airfoil has a plurality of cooling air passages extending linearly from the root portion to the tip portion of the airfoil. The blade includes a shank having a pair of cavities in communication through the blade dovetail with a plenum in the wheel space for supplying cooling air to the passages in the airfoil. The cooling passages in the airfoil terminate in a recess at the tip portion which has an opening adjacent the trailing edge of the airfoil and along the suction side to enable egress of cooling air into the hot gas stream on the low pressure side of the airfoil. The majority of the cooling passages are turbulated. Certain of those passages are arranged in rows lying adjacent to the pressure and suction sides of the airfoil.</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>1999</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZLAJKS1KysxLVUjKSUxJVSjPLMlQSM3LSMxLTk1RSM7Pz8nMS1dIzEtRKCjKT8vMSVXILyjJzM2sSizJzM_jYWBNS8wpTuWF0twM8m6uIc4euqkF-fGpxQWJyal5qSXxocGmlhYGRgaWjsaEVQAAQD0vaA</recordid><startdate>19991109</startdate><enddate>19991109</enddate><creator>GREGORY; BRENT A</creator><creator>BARRY; VINCENT ANTHONY</creator><creator>ABUAF; NESIM</creator><scope>EVB</scope></search><sort><creationdate>19991109</creationdate><title>Turbine blade with enhanced cooling and profile optimization</title><author>GREGORY; BRENT A ; BARRY; VINCENT ANTHONY ; ABUAF; NESIM</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US5980209A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>1999</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>GREGORY; BRENT A</creatorcontrib><creatorcontrib>BARRY; VINCENT ANTHONY</creatorcontrib><creatorcontrib>ABUAF; NESIM</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>GREGORY; BRENT A</au><au>BARRY; VINCENT ANTHONY</au><au>ABUAF; NESIM</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Turbine blade with enhanced cooling and profile optimization</title><date>1999-11-09</date><risdate>1999</risdate><abstract>A first-stage turbine blade includes an airfoil having a profile according to Table I. The airfoil has a plurality of cooling air passages extending linearly from the root portion to the tip portion of the airfoil. The blade includes a shank having a pair of cavities in communication through the blade dovetail with a plenum in the wheel space for supplying cooling air to the passages in the airfoil. The cooling passages in the airfoil terminate in a recess at the tip portion which has an opening adjacent the trailing edge of the airfoil and along the suction side to enable egress of cooling air into the hot gas stream on the low pressure side of the airfoil. The majority of the cooling passages are turbulated. Certain of those passages are arranged in rows lying adjacent to the pressure and suction sides of the airfoil.</abstract><edition>6</edition><oa>free_for_read</oa></addata></record> |
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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 | Turbine blade with enhanced cooling and profile optimization |
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