HIGH PRESSURE COMPRESSOR AUGMENTED BLEED WITH AUTONOMOUSLY ACTUATED VALVE
PROBLEM TO BE SOLVED: To provide a gas turbine engine compressor bleed system allowing cruise bleed to meet plenum pressurization requirements using a lower pressure compressor stage.SOLUTION: A compressor bleed assembly 40 comprises: an annular bleed plenum 43 radially disposed between outer and in...
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| creator | MICHAEL ANTHONY THOMAS JR CURTIS WILLIAM MOECKEL CARLOS IVAN FLORES DAVID WILLIAM FASIG |
| description | PROBLEM TO BE SOLVED: To provide a gas turbine engine compressor bleed system allowing cruise bleed to meet plenum pressurization requirements using a lower pressure compressor stage.SOLUTION: A compressor bleed assembly 40 comprises: an annular bleed plenum 43 radially disposed between outer and inner casings 50, 52; and upstream and downstream bleed ports 54, 56 disposed radially between a compressor flowpath 39 and the bleed plenum at upstream and downstream stages 44, 46 of a compressor 18. A bleed path 62 extends from the downstream bleed port through the bleed plenum and out of a bleed outlet 42. An autonomously actuated valve 60 is disposed in the bleed path or downstream bleed port, and may be opened at take-off and/or climb. The bleed outlet may be an engine bleed outlet disposed radially through the outer casing and in fluid communication with the bleed plenum. The bleed path extends from the downstream bleed port through the plenum and out of a forward bleed outlet.SELECTED DRAWING: Figure 2
【課題】より低圧の圧縮機段を使用して巡航抽気がプレナム加圧要件を満たすのを可能にするガスタービンエンジンの圧縮機抽気システムを提供する。【解決手段】圧縮機抽気組立体４０は、外側及び内側ケーシング５０、５２の間に半径方向に配置された環状抽気プレナム４３と、圧縮機１８の上流及び下流段４４、４６において、圧縮機流路３９と抽気プレナムとの間で半径方向配置された上流及び下流抽気ポート５４、５６とを含む。抽気経路６２は、下流抽気ポートから延び、抽気プレナムを通って抽気出口４２から外に出る。自律作動弁６０は、抽気経路又は下流抽気ポートに配置され、離陸時／上昇時に開放することができる。抽気出口は、外側ケーシングを貫通して半径方向に設けられ、抽気プレナムと流体連通する、エンジン抽気出口とすることができる。抽気経路は、下流抽気ポートから延び、プレナムを通って、前方抽気出口から外に出る。【選択図】図２ |
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【課題】より低圧の圧縮機段を使用して巡航抽気がプレナム加圧要件を満たすのを可能にするガスタービンエンジンの圧縮機抽気システムを提供する。【解決手段】圧縮機抽気組立体４０は、外側及び内側ケーシング５０、５２の間に半径方向に配置された環状抽気プレナム４３と、圧縮機１８の上流及び下流段４４、４６において、圧縮機流路３９と抽気プレナムとの間で半径方向配置された上流及び下流抽気ポート５４、５６とを含む。抽気経路６２は、下流抽気ポートから延び、抽気プレナムを通って抽気出口４２から外に出る。自律作動弁６０は、抽気経路又は下流抽気ポートに配置され、離陸時／上昇時に開放することができる。抽気出口は、外側ケーシングを貫通して半径方向に設けられ、抽気プレナムと流体連通する、エンジン抽気出口とすることができる。抽気経路は、下流抽気ポートから延び、プレナムを通って、前方抽気出口から外に出る。【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 ; 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>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=20170907&DB=EPODOC&CC=JP&NR=2017155746A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25562,76317</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20170907&DB=EPODOC&CC=JP&NR=2017155746A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>MICHAEL ANTHONY THOMAS JR</creatorcontrib><creatorcontrib>CURTIS WILLIAM MOECKEL</creatorcontrib><creatorcontrib>CARLOS IVAN FLORES</creatorcontrib><creatorcontrib>DAVID WILLIAM FASIG</creatorcontrib><title>HIGH PRESSURE COMPRESSOR AUGMENTED BLEED WITH AUTONOMOUSLY ACTUATED VALVE</title><description>PROBLEM TO BE SOLVED: To provide a gas turbine engine compressor bleed system allowing cruise bleed to meet plenum pressurization requirements using a lower pressure compressor stage.SOLUTION: A compressor bleed assembly 40 comprises: an annular bleed plenum 43 radially disposed between outer and inner casings 50, 52; and upstream and downstream bleed ports 54, 56 disposed radially between a compressor flowpath 39 and the bleed plenum at upstream and downstream stages 44, 46 of a compressor 18. A bleed path 62 extends from the downstream bleed port through the bleed plenum and out of a bleed outlet 42. An autonomously actuated valve 60 is disposed in the bleed path or downstream bleed port, and may be opened at take-off and/or climb. The bleed outlet may be an engine bleed outlet disposed radially through the outer casing and in fluid communication with the bleed plenum. The bleed path extends from the downstream bleed port through the plenum and out of a forward bleed outlet.SELECTED DRAWING: Figure 2
【課題】より低圧の圧縮機段を使用して巡航抽気がプレナム加圧要件を満たすのを可能にするガスタービンエンジンの圧縮機抽気システムを提供する。【解決手段】圧縮機抽気組立体４０は、外側及び内側ケーシング５０、５２の間に半径方向に配置された環状抽気プレナム４３と、圧縮機１８の上流及び下流段４４、４６において、圧縮機流路３９と抽気プレナムとの間で半径方向配置された上流及び下流抽気ポート５４、５６とを含む。抽気経路６２は、下流抽気ポートから延び、抽気プレナムを通って抽気出口４２から外に出る。自律作動弁６０は、抽気経路又は下流抽気ポートに配置され、離陸時／上昇時に開放することができる。抽気出口は、外側ケーシングを貫通して半径方向に設けられ、抽気プレナムと流体連通する、エンジン抽気出口とすることができる。抽気経路は、下流抽気ポートから延び、プレナムを通って、前方抽気出口から外に出る。【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>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>2017</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZPD08HT3UAgIcg0ODg1yVXD29wWz_YMUHEPdfV39QlxdFJx8XIFkuGeIB1AwxN_P39c_NNgnUsHROSTUEaQgzNEnzJWHgTUtMac4lRdKczMoubmGOHvophbkx6cWFyQmp-allsR7BRgZGJobmpqam5g5GhOlCADF9y4Q</recordid><startdate>20170907</startdate><enddate>20170907</enddate><creator>MICHAEL ANTHONY THOMAS JR</creator><creator>CURTIS WILLIAM MOECKEL</creator><creator>CARLOS IVAN FLORES</creator><creator>DAVID WILLIAM FASIG</creator><scope>EVB</scope></search><sort><creationdate>20170907</creationdate><title>HIGH PRESSURE COMPRESSOR AUGMENTED BLEED WITH AUTONOMOUSLY ACTUATED VALVE</title><author>MICHAEL ANTHONY THOMAS JR ; CURTIS WILLIAM MOECKEL ; CARLOS IVAN FLORES ; DAVID WILLIAM FASIG</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_JP2017155746A3</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>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>MICHAEL ANTHONY THOMAS JR</creatorcontrib><creatorcontrib>CURTIS WILLIAM MOECKEL</creatorcontrib><creatorcontrib>CARLOS IVAN FLORES</creatorcontrib><creatorcontrib>DAVID WILLIAM FASIG</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>MICHAEL ANTHONY THOMAS JR</au><au>CURTIS WILLIAM MOECKEL</au><au>CARLOS IVAN FLORES</au><au>DAVID WILLIAM FASIG</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>HIGH PRESSURE COMPRESSOR AUGMENTED BLEED WITH AUTONOMOUSLY ACTUATED VALVE</title><date>2017-09-07</date><risdate>2017</risdate><abstract>PROBLEM TO BE SOLVED: To provide a gas turbine engine compressor bleed system allowing cruise bleed to meet plenum pressurization requirements using a lower pressure compressor stage.SOLUTION: A compressor bleed assembly 40 comprises: an annular bleed plenum 43 radially disposed between outer and inner casings 50, 52; and upstream and downstream bleed ports 54, 56 disposed radially between a compressor flowpath 39 and the bleed plenum at upstream and downstream stages 44, 46 of a compressor 18. A bleed path 62 extends from the downstream bleed port through the bleed plenum and out of a bleed outlet 42. An autonomously actuated valve 60 is disposed in the bleed path or downstream bleed port, and may be opened at take-off and/or climb. The bleed outlet may be an engine bleed outlet disposed radially through the outer casing and in fluid communication with the bleed plenum. The bleed path extends from the downstream bleed port through the plenum and out of a forward bleed outlet.SELECTED DRAWING: Figure 2
【課題】より低圧の圧縮機段を使用して巡航抽気がプレナム加圧要件を満たすのを可能にするガスタービンエンジンの圧縮機抽気システムを提供する。【解決手段】圧縮機抽気組立体４０は、外側及び内側ケーシング５０、５２の間に半径方向に配置された環状抽気プレナム４３と、圧縮機１８の上流及び下流段４４、４６において、圧縮機流路３９と抽気プレナムとの間で半径方向配置された上流及び下流抽気ポート５４、５６とを含む。抽気経路６２は、下流抽気ポートから延び、抽気プレナムを通って抽気出口４２から外に出る。自律作動弁６０は、抽気経路又は下流抽気ポートに配置され、離陸時／上昇時に開放することができる。抽気出口は、外側ケーシングを貫通して半径方向に設けられ、抽気プレナムと流体連通する、エンジン抽気出口とすることができる。抽気経路は、下流抽気ポートから延び、プレナムを通って、前方抽気出口から外に出る。【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 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 | HIGH PRESSURE COMPRESSOR AUGMENTED BLEED WITH AUTONOMOUSLY ACTUATED VALVE |
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