TURBINE FRAME COOLING SYSTEMS AND METHODS OF ASSEMBLY FOR USE IN GAS TURBINE ENGINE
PROBLEM TO BE SOLVED: To provide turbine frame cooling systems for use in a gas turbine engine.SOLUTION: A turbine frame cooling system 100 includes an outer ring 102 defining a cavity 118, and a hub 104 positioned radially inward of the outer ring. The turbine frame cooling system 100 also includes...
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| creator | KENNETH JAY MOORE LACHAPELLE DONALD GEORGE BRADFORD ALAN TRACEY THOMAS LIPINSKI STEPHEN JOSEPH WAYMEYER |
| description | PROBLEM TO BE SOLVED: To provide turbine frame cooling systems for use in a gas turbine engine.SOLUTION: A turbine frame cooling system 100 includes an outer ring 102 defining a cavity 118, and a hub 104 positioned radially inward of the outer ring. The turbine frame cooling system 100 also includes a plurality of circumferentially spaced first fairings 106 coupled between the outer ring 102 and the hub 104, and a plurality of circumferentially spaced second fairings 108 coupled between the outer ring 102 and the hub 104, where the first and second fairings 106, 108 are alternatingly positioned with the hub 104. The turbine frame cooling system 100 also includes a plurality of circumferentially spaced air scoops 116 coupled to the outer ring 102. The plurality of air scoops 116 extend into a bypass duct 40 and are configured to channel a bypass air cooling flow into the cavity 118 of the outer ring 102.SELECTED DRAWING: Figure 2
【課題】ガスタービンエンジン用途のタービンフレーム冷却システムを提供する。【解決手段】タービンフレーム冷却システム１００はキャビティ１１８を画定する外側リング１０２および外側リング内部に放射状に配置されるハブ１０４を備える。タービンフレーム冷却システム１００は、外側リング１０２とハブ１０４との間で連結した複数の外周にスペースを置いた第一フェアリング１０６および外側リング１０２とハブ１０４との間で連結した複数の外周にスペースを置いた第二フェアリング１０８も備え、第一および第二フェアリング１０６、１０８はハブ１０４と交互に配置される。タービンフレーム冷却システム１００は、外側リング１０２と連結した複数の外周にスペースを置いたエアスクープ１１６も備え、複数のエアスクープ１１６はバイパスダクト４０の中に伸び、バイパスエアー冷却フローを外側リング１０２のキャビティ１１８中に誘導するように構成される。【選択図】図２ |
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【課題】ガスタービンエンジン用途のタービンフレーム冷却システムを提供する。【解決手段】タービンフレーム冷却システム１００はキャビティ１１８を画定する外側リング１０２および外側リング内部に放射状に配置されるハブ１０４を備える。タービンフレーム冷却システム１００は、外側リング１０２とハブ１０４との間で連結した複数の外周にスペースを置いた第一フェアリング１０６および外側リング１０２とハブ１０４との間で連結した複数の外周にスペースを置いた第二フェアリング１０８も備え、第一および第二フェアリング１０６、１０８はハブ１０４と交互に配置される。タービンフレーム冷却システム１００は、外側リング１０２と連結した複数の外周にスペースを置いたエアスクープ１１６も備え、複数のエアスクープ１１６はバイパスダクト４０の中に伸び、バイパスエアー冷却フローを外側リング１０２のキャビティ１１８中に誘導するように構成される。【選択図】図２</description><language>eng ; jpn</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 ; JET-PROPULSION PLANTS ; LIGHTING ; MACHINES OR ENGINES IN GENERAL ; MECHANICAL ENGINEERING ; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES ; STEAM ENGINES ; WEAPONS</subject><creationdate>2017</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=20170817&DB=EPODOC&CC=JP&NR=2017141807A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20170817&DB=EPODOC&CC=JP&NR=2017141807A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>KENNETH JAY MOORE</creatorcontrib><creatorcontrib>LACHAPELLE DONALD GEORGE</creatorcontrib><creatorcontrib>BRADFORD ALAN TRACEY</creatorcontrib><creatorcontrib>THOMAS LIPINSKI</creatorcontrib><creatorcontrib>STEPHEN JOSEPH WAYMEYER</creatorcontrib><title>TURBINE FRAME COOLING SYSTEMS AND METHODS OF ASSEMBLY FOR USE IN GAS TURBINE ENGINE</title><description>PROBLEM TO BE SOLVED: To provide turbine frame cooling systems for use in a gas turbine engine.SOLUTION: A turbine frame cooling system 100 includes an outer ring 102 defining a cavity 118, and a hub 104 positioned radially inward of the outer ring. The turbine frame cooling system 100 also includes a plurality of circumferentially spaced first fairings 106 coupled between the outer ring 102 and the hub 104, and a plurality of circumferentially spaced second fairings 108 coupled between the outer ring 102 and the hub 104, where the first and second fairings 106, 108 are alternatingly positioned with the hub 104. The turbine frame cooling system 100 also includes a plurality of circumferentially spaced air scoops 116 coupled to the outer ring 102. The plurality of air scoops 116 extend into a bypass duct 40 and are configured to channel a bypass air cooling flow into the cavity 118 of the outer ring 102.SELECTED DRAWING: Figure 2
【課題】ガスタービンエンジン用途のタービンフレーム冷却システムを提供する。【解決手段】タービンフレーム冷却システム１００はキャビティ１１８を画定する外側リング１０２および外側リング内部に放射状に配置されるハブ１０４を備える。タービンフレーム冷却システム１００は、外側リング１０２とハブ１０４との間で連結した複数の外周にスペースを置いた第一フェアリング１０６および外側リング１０２とハブ１０４との間で連結した複数の外周にスペースを置いた第二フェアリング１０８も備え、第一および第二フェアリング１０６、１０８はハブ１０４と交互に配置される。タービンフレーム冷却システム１００は、外側リング１０２と連結した複数の外周にスペースを置いたエアスクープ１１６も備え、複数のエアスクープ１１６はバイパスダクト４０の中に伸び、バイパスエアー冷却フローを外側リング１０２のキャビティ１１８中に誘導するように構成される。【選択図】図２</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>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>2017</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZAgOCQ1y8vRzVXALcvR1VXD29_fx9HNXCI4MDnH1DVZw9HNR8HUN8fB3CVbwd1NwDA529XXyiVRw8w9SCA12VfD0U3B3DFaAGeLq5w6keBhY0xJzilN5oTQ3g5Kba4izh25qQX58anFBYnJqXmpJvFeAkYGhuaGJoYWBuaMxUYoAQTgwBA</recordid><startdate>20170817</startdate><enddate>20170817</enddate><creator>KENNETH JAY MOORE</creator><creator>LACHAPELLE DONALD GEORGE</creator><creator>BRADFORD ALAN TRACEY</creator><creator>THOMAS LIPINSKI</creator><creator>STEPHEN JOSEPH WAYMEYER</creator><scope>EVB</scope></search><sort><creationdate>20170817</creationdate><title>TURBINE FRAME COOLING SYSTEMS AND METHODS OF ASSEMBLY FOR USE IN GAS TURBINE ENGINE</title><author>KENNETH JAY MOORE ; LACHAPELLE DONALD GEORGE ; BRADFORD ALAN TRACEY ; THOMAS LIPINSKI ; STEPHEN JOSEPH WAYMEYER</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_JP2017141807A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; jpn</language><creationdate>2017</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>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>KENNETH JAY MOORE</creatorcontrib><creatorcontrib>LACHAPELLE DONALD GEORGE</creatorcontrib><creatorcontrib>BRADFORD ALAN TRACEY</creatorcontrib><creatorcontrib>THOMAS LIPINSKI</creatorcontrib><creatorcontrib>STEPHEN JOSEPH WAYMEYER</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>KENNETH JAY MOORE</au><au>LACHAPELLE DONALD GEORGE</au><au>BRADFORD ALAN TRACEY</au><au>THOMAS LIPINSKI</au><au>STEPHEN JOSEPH WAYMEYER</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>TURBINE FRAME COOLING SYSTEMS AND METHODS OF ASSEMBLY FOR USE IN GAS TURBINE ENGINE</title><date>2017-08-17</date><risdate>2017</risdate><abstract>PROBLEM TO BE SOLVED: To provide turbine frame cooling systems for use in a gas turbine engine.SOLUTION: A turbine frame cooling system 100 includes an outer ring 102 defining a cavity 118, and a hub 104 positioned radially inward of the outer ring. The turbine frame cooling system 100 also includes a plurality of circumferentially spaced first fairings 106 coupled between the outer ring 102 and the hub 104, and a plurality of circumferentially spaced second fairings 108 coupled between the outer ring 102 and the hub 104, where the first and second fairings 106, 108 are alternatingly positioned with the hub 104. The turbine frame cooling system 100 also includes a plurality of circumferentially spaced air scoops 116 coupled to the outer ring 102. The plurality of air scoops 116 extend into a bypass duct 40 and are configured to channel a bypass air cooling flow into the cavity 118 of the outer ring 102.SELECTED DRAWING: Figure 2
【課題】ガスタービンエンジン用途のタービンフレーム冷却システムを提供する。【解決手段】タービンフレーム冷却システム１００はキャビティ１１８を画定する外側リング１０２および外側リング内部に放射状に配置されるハブ１０４を備える。タービンフレーム冷却システム１００は、外側リング１０２とハブ１０４との間で連結した複数の外周にスペースを置いた第一フェアリング１０６および外側リング１０２とハブ１０４との間で連結した複数の外周にスペースを置いた第二フェアリング１０８も備え、第一および第二フェアリング１０６、１０８はハブ１０４と交互に配置される。タービンフレーム冷却システム１００は、外側リング１０２と連結した複数の外周にスペースを置いたエアスクープ１１６も備え、複数のエアスクープ１１６はバイパスダクト４０の中に伸び、バイパスエアー冷却フローを外側リング１０２のキャビティ１１８中に誘導するように構成される。【選択図】図２</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 JET-PROPULSION PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS |
| title | TURBINE FRAME COOLING SYSTEMS AND METHODS OF ASSEMBLY FOR USE IN GAS TURBINE ENGINE |
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