Rotary Pressure Rise Combustor For A Gas Turbine Engine
A gas generator for providing continuous pressure rise combustion, including: a rotatable member including a forward end, an aft end, a circumferential wall and a longitudinal centerline axis extending therethrough; an outer circumferential wall, wherein the rotatable member is positioned therein so...
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| creator | GIFFIN, III ROLLIN GEORGE FRANER MATTHEW TIMOTHY MURROW KURT DAVID |
| description | A gas generator for providing continuous pressure rise combustion, including: a rotatable member including a forward end, an aft end, a circumferential wall and a longitudinal centerline axis extending therethrough; an outer circumferential wall, wherein the rotatable member is positioned therein so that the circumferential wall of the rotatable member is spaced radially inwardly from the outer circumferential wall; at least one helical channel formed by a plurality of helical sidewalls extending between the circumferential wall of the rotatable member and the outer circumferential wall, each helical channel being open at the forward end and the aft end of the rotatable member so as to provide flow communication therethrough; an air supply for providing air to each helical channel; and, a fuel supply for providing fuel to each helical channel. Each helical channel includes an inlet portion having a first cross-sectional area for receiving a flow having a designated shape and orientation, a throat portion downstream of the inlet portion having a second cross-section less than the first cross-section of the inlet portion, and a diffusion portion downstream of the throat portion having a third cross-section greater than the second cross-section of the throat portion. A device is also positioned downstream from the diffusion portion of each helical channel for holding flame therein. A mixture of the fuel and air is continuously combusted downstream of the diffusion portion of each helical channel in a manner such that combustion gases exit therefrom with an increased pressure and temperature. |
| format | Patent |
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Each helical channel includes an inlet portion having a first cross-sectional area for receiving a flow having a designated shape and orientation, a throat portion downstream of the inlet portion having a second cross-section less than the first cross-section of the inlet portion, and a diffusion portion downstream of the throat portion having a third cross-section greater than the second cross-section of the throat portion. A device is also positioned downstream from the diffusion portion of each helical channel for holding flame therein. A mixture of the fuel and air is continuously combusted downstream of the diffusion portion of each helical channel in a manner such that combustion gases exit therefrom with an increased pressure and temperature.</description><language>eng</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 ; INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS ; INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 ; 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>2009</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=20090806&DB=EPODOC&CC=US&NR=2009196733A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,309,781,886,25569,76552</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20090806&DB=EPODOC&CC=US&NR=2009196733A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>GIFFIN, III ROLLIN GEORGE</creatorcontrib><creatorcontrib>FRANER MATTHEW TIMOTHY</creatorcontrib><creatorcontrib>MURROW KURT DAVID</creatorcontrib><title>Rotary Pressure Rise Combustor For A Gas Turbine Engine</title><description>A gas generator for providing continuous pressure rise combustion, including: a rotatable member including a forward end, an aft end, a circumferential wall and a longitudinal centerline axis extending therethrough; an outer circumferential wall, wherein the rotatable member is positioned therein so that the circumferential wall of the rotatable member is spaced radially inwardly from the outer circumferential wall; at least one helical channel formed by a plurality of helical sidewalls extending between the circumferential wall of the rotatable member and the outer circumferential wall, each helical channel being open at the forward end and the aft end of the rotatable member so as to provide flow communication therethrough; an air supply for providing air to each helical channel; and, a fuel supply for providing fuel to each helical channel. Each helical channel includes an inlet portion having a first cross-sectional area for receiving a flow having a designated shape and orientation, a throat portion downstream of the inlet portion having a second cross-section less than the first cross-section of the inlet portion, and a diffusion portion downstream of the throat portion having a third cross-section greater than the second cross-section of the throat portion. A device is also positioned downstream from the diffusion portion of each helical channel for holding flame therein. A mixture of the fuel and air is continuously combusted downstream of the diffusion portion of each helical channel in a manner such that combustion gases exit therefrom with an increased pressure and temperature.</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>INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS</subject><subject>INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04</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>2009</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZDAPyi9JLKpUCChKLS4uLUpVCMosTlVwzs9NKi0uyS9ScANiRwX3xGKFkNKipMy8VAXXvHQgxcPAmpaYU5zKC6W5GZTdXEOcPXRTC_LjU4sLEpNT81JL4kODjQwMLA0tzcyNjR0NjYlTBQAoyC3_</recordid><startdate>20090806</startdate><enddate>20090806</enddate><creator>GIFFIN, III ROLLIN GEORGE</creator><creator>FRANER MATTHEW TIMOTHY</creator><creator>MURROW KURT DAVID</creator><scope>EVB</scope></search><sort><creationdate>20090806</creationdate><title>Rotary Pressure Rise Combustor For A Gas Turbine Engine</title><author>GIFFIN, III ROLLIN GEORGE ; FRANER MATTHEW TIMOTHY ; MURROW KURT DAVID</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US2009196733A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2009</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>INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS</topic><topic>INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04</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>GIFFIN, III ROLLIN GEORGE</creatorcontrib><creatorcontrib>FRANER MATTHEW TIMOTHY</creatorcontrib><creatorcontrib>MURROW KURT DAVID</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>GIFFIN, III ROLLIN GEORGE</au><au>FRANER MATTHEW TIMOTHY</au><au>MURROW KURT DAVID</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Rotary Pressure Rise Combustor For A Gas Turbine Engine</title><date>2009-08-06</date><risdate>2009</risdate><abstract>A gas generator for providing continuous pressure rise combustion, including: a rotatable member including a forward end, an aft end, a circumferential wall and a longitudinal centerline axis extending therethrough; an outer circumferential wall, wherein the rotatable member is positioned therein so that the circumferential wall of the rotatable member is spaced radially inwardly from the outer circumferential wall; at least one helical channel formed by a plurality of helical sidewalls extending between the circumferential wall of the rotatable member and the outer circumferential wall, each helical channel being open at the forward end and the aft end of the rotatable member so as to provide flow communication therethrough; an air supply for providing air to each helical channel; and, a fuel supply for providing fuel to each helical channel. Each helical channel includes an inlet portion having a first cross-sectional area for receiving a flow having a designated shape and orientation, a throat portion downstream of the inlet portion having a second cross-section less than the first cross-section of the inlet portion, and a diffusion portion downstream of the throat portion having a third cross-section greater than the second cross-section of the throat portion. A device is also positioned downstream from the diffusion portion of each helical channel for holding flame therein. A mixture of the fuel and air is continuously combusted downstream of the diffusion portion of each helical channel in a manner such that combustion gases exit therefrom with an increased pressure and temperature.</abstract><oa>free_for_read</oa></addata></record> |
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| language | eng |
| recordid | cdi_epo_espacenet_US2009196733A1 |
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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 INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 JET-PROPULSION PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS |
| title | Rotary Pressure Rise Combustor For A Gas Turbine Engine |
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