STEUERSYSTEM FUER EINEN MEHRSTUFIGEN AXIALSTROEMUNGSKOMPRESSOR EINES GASTURBINENTRIEBWERKS
A control system is provided for the multi-stage axial flow compressor of a gas turbine engine. The control system embraces a stage of variable angle guide vanes, a first detector adapted to detect a first pressure in the compressor which is influenced by the vane angular setting, and a second detec...
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| creator | GEORGE RADCLIFFE,ALAN GRAHAM FARRAR,PETER GORDON |
| description | A control system is provided for the multi-stage axial flow compressor of a gas turbine engine. The control system embraces a stage of variable angle guide vanes, a first detector adapted to detect a first pressure in the compressor which is influenced by the vane angular setting, and a second detector adapted to detect a second pressure independent of the vane setting but bearing a functional relationship to the rotational speed of a compressor of the engine. A control unit is adapted to use the pressures detected by the detectors to cause an actuation mechanism to adjust the angular setting of the guide vanes in a predetermined manner dependent upon the ratio of the second pressure to the first pressure. |
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The control system embraces a stage of variable angle guide vanes, a first detector adapted to detect a first pressure in the compressor which is influenced by the vane angular setting, and a second detector adapted to detect a second pressure independent of the vane setting but bearing a functional relationship to the rotational speed of a compressor of the engine. A control unit is adapted to use the pressures detected by the detectors to cause an actuation mechanism to adjust the angular setting of the guide vanes in a predetermined manner dependent upon the ratio of the second pressure to the first pressure.</description><edition>2</edition><language>ger</language><subject>AIR INTAKES FOR JET-PROPULSION PLANTS ; BLASTING ; COMBUSTION ENGINES ; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ; GAS-TURBINE PLANTS ; HEATING ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; LIGHTING ; MECHANICAL ENGINEERING ; NON-POSITIVE DISPLACEMENT PUMPS ; POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS ; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS ; WEAPONS</subject><creationdate>1979</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=19790920&DB=EPODOC&CC=DE&NR=2909825A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25542,76289</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=19790920&DB=EPODOC&CC=DE&NR=2909825A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>GEORGE RADCLIFFE,ALAN</creatorcontrib><creatorcontrib>GRAHAM FARRAR,PETER GORDON</creatorcontrib><title>STEUERSYSTEM FUER EINEN MEHRSTUFIGEN AXIALSTROEMUNGSKOMPRESSOR EINES GASTURBINENTRIEBWERKS</title><description>A control system is provided for the multi-stage axial flow compressor of a gas turbine engine. The control system embraces a stage of variable angle guide vanes, a first detector adapted to detect a first pressure in the compressor which is influenced by the vane angular setting, and a second detector adapted to detect a second pressure independent of the vane setting but bearing a functional relationship to the rotational speed of a compressor of the engine. A control unit is adapted to use the pressures detected by the detectors to cause an actuation mechanism to adjust the angular setting of the guide vanes in a predetermined manner dependent upon the ratio of the second pressure to the first pressure.</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>GAS-TURBINE PLANTS</subject><subject>HEATING</subject><subject>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</subject><subject>LIGHTING</subject><subject>MECHANICAL ENGINEERING</subject><subject>NON-POSITIVE DISPLACEMENT PUMPS</subject><subject>POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS</subject><subject>PUMPS FOR LIQUIDS OR ELASTIC FLUIDS</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>1979</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZIgKDnENdQ0KjgTSvgpuQKaCq6efq5-Cr6tHUHBIqJunO5DjGOHp6BMcEuTv6hvq5x7s7e8bEOQaHOwPURys4O4IVBrkBNIYEuTp6hTuGuQdzMPAmpaYU5zKC6W5GRTcXEOcPXRTC_LjU4sLEpNT81JL4l1cjSwNLC2MTB0NjYlQAgCxRjLZ</recordid><startdate>19790920</startdate><enddate>19790920</enddate><creator>GEORGE RADCLIFFE,ALAN</creator><creator>GRAHAM FARRAR,PETER GORDON</creator><scope>EVB</scope></search><sort><creationdate>19790920</creationdate><title>STEUERSYSTEM FUER EINEN MEHRSTUFIGEN AXIALSTROEMUNGSKOMPRESSOR EINES GASTURBINENTRIEBWERKS</title><author>GEORGE RADCLIFFE,ALAN ; GRAHAM FARRAR,PETER GORDON</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_DE2909825A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>ger</language><creationdate>1979</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>GAS-TURBINE PLANTS</topic><topic>HEATING</topic><topic>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</topic><topic>LIGHTING</topic><topic>MECHANICAL ENGINEERING</topic><topic>NON-POSITIVE DISPLACEMENT PUMPS</topic><topic>POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS</topic><topic>PUMPS FOR LIQUIDS OR ELASTIC FLUIDS</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>GEORGE RADCLIFFE,ALAN</creatorcontrib><creatorcontrib>GRAHAM FARRAR,PETER GORDON</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>GEORGE RADCLIFFE,ALAN</au><au>GRAHAM FARRAR,PETER GORDON</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>STEUERSYSTEM FUER EINEN MEHRSTUFIGEN AXIALSTROEMUNGSKOMPRESSOR EINES GASTURBINENTRIEBWERKS</title><date>1979-09-20</date><risdate>1979</risdate><abstract>A control system is provided for the multi-stage axial flow compressor of a gas turbine engine. The control system embraces a stage of variable angle guide vanes, a first detector adapted to detect a first pressure in the compressor which is influenced by the vane angular setting, and a second detector adapted to detect a second pressure independent of the vane setting but bearing a functional relationship to the rotational speed of a compressor of the engine. A control unit is adapted to use the pressures detected by the detectors to cause an actuation mechanism to adjust the angular setting of the guide vanes in a predetermined manner dependent upon the ratio of the second pressure to the first pressure.</abstract><edition>2</edition><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 GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT PUMPS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS WEAPONS |
| title | STEUERSYSTEM FUER EINEN MEHRSTUFIGEN AXIALSTROEMUNGSKOMPRESSOR EINES GASTURBINENTRIEBWERKS |
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