TURBOJET ENGINE LOW-PRESSURE COMPRESSOR FIRST STAGE ROTOR IMPELLER (VERSIONS)
FIELD: engines and pumps.SUBSTANCE: invention relates to engine building. Rotor first stage impeller, including jet turbine engine (JTE) low pressure compressor (LPC) drum-disc design shaft comprises disc equipped with slots, and blade ring, wherein disc is made in form of one-piece element includin...
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| creator | Erichev Dmitrij JUrevich Marchukov Evgenij JUvenalevich Artjukhov Aleksandr Viktorovich Poljakov Konstantin Sergeevich Uzbekov Andrej Valerevich Manapov Irik Usmanovich Kuznetsov Igor Sergeevich |
| description | FIELD: engines and pumps.SUBSTANCE: invention relates to engine building. Rotor first stage impeller, including jet turbine engine (JTE) low pressure compressor (LPC) drum-disc design shaft comprises disc equipped with slots, and blade ring, wherein disc is made in form of one-piece element including hub with central hole, web and rim, and blades each contain tail and wing with profile formed by concave pressure side and convex back, coupled by inlet and outlet edges. Disc web is made with variable in height section, conically narrowing from hub to rim with gradient of Gthickness reducing in specified direction, equal to G=(δ-δ)/H=(0.11÷0.15) [m/m], where δis disc web peripheral part thickness; δis web root part thickness; His disc web radial height between sections of connections with hub and rim. Hub is made integral with rotor shaft front bearing trunnion developed on one side to LPC inlet and made with variable diameter, gradually decreasing at least in two projections from disc web to trunnion support end section. Wheel rim outer surface is made composing internal circuit flow section axial section with axial length equal to rim generatrix projection on rotor shaft axis, and with radius increasing in LPC axial cross-section towards working fluid flow, wherein rim is connected with disc web to make front and rear circular conical flanges. Rear flange is provided with annular element made for for subsequent permanent connection with second stage disc web front flange, and grooves are uniformly spaced apart along wheel rim perimeter with angular frequency Y=(4.6÷6.2) [unit/rad] and are made with mutually inclined side edges, having in cross section configuration of lock joint with blade root element. Slots for fitting blade roots are uniformly spaced apart along disc rim perimeter, wherein each slot foot is located in plane parallel to rotor shaft axis, and groove bottom longitudinal axis makes with rotor shaft axis in projection on said plane angle of α blade shank installation, defined in range of values α=(16÷22)°, and root inlet and outlet edges are made diverging to peripheral blade end with gradient Gtheir connecting chord increase, equal to G=(L-L)/H=(9.3÷13.3)·10[m/m], where Lis peripheral chord length connecting blade body inlet and outlet edges in conditional plane perpendicular to blade body axis; Lis same, root chord length; His blade body average height.EFFECT: invention allows to increase efficiency and increase gas-dynamic stability margin |
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| fullrecord | <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_RU2603382C1</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>RU2603382C1</sourcerecordid><originalsourceid>FETCH-epo_espacenet_RU2603382C13</originalsourceid><addsrcrecordid>eNrjZPANCQ1y8vdyDVFw9XP39HNV8PEP1w0Icg0ODg1yVXD29wWz_YMU3DyDgkMUgkMc3V0VgvxDgCKevgGuPj6uQQoaYa5BwZ7-fsGaPAysaYk5xam8UJqbQcHNNcTZQze1ID8-tbggMTk1L7UkPijUyMzA2NjCyNnQmAglANe3LnQ</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>TURBOJET ENGINE LOW-PRESSURE COMPRESSOR FIRST STAGE ROTOR IMPELLER (VERSIONS)</title><source>esp@cenet</source><creator>Erichev Dmitrij JUrevich ; Marchukov Evgenij JUvenalevich ; Artjukhov Aleksandr Viktorovich ; Poljakov Konstantin Sergeevich ; Uzbekov Andrej Valerevich ; Manapov Irik Usmanovich ; Kuznetsov Igor Sergeevich</creator><creatorcontrib>Erichev Dmitrij JUrevich ; Marchukov Evgenij JUvenalevich ; Artjukhov Aleksandr Viktorovich ; Poljakov Konstantin Sergeevich ; Uzbekov Andrej Valerevich ; Manapov Irik Usmanovich ; Kuznetsov Igor Sergeevich</creatorcontrib><description>FIELD: engines and pumps.SUBSTANCE: invention relates to engine building. Rotor first stage impeller, including jet turbine engine (JTE) low pressure compressor (LPC) drum-disc design shaft comprises disc equipped with slots, and blade ring, wherein disc is made in form of one-piece element including hub with central hole, web and rim, and blades each contain tail and wing with profile formed by concave pressure side and convex back, coupled by inlet and outlet edges. Disc web is made with variable in height section, conically narrowing from hub to rim with gradient of Gthickness reducing in specified direction, equal to G=(δ-δ)/H=(0.11÷0.15) [m/m], where δis disc web peripheral part thickness; δis web root part thickness; His disc web radial height between sections of connections with hub and rim. Hub is made integral with rotor shaft front bearing trunnion developed on one side to LPC inlet and made with variable diameter, gradually decreasing at least in two projections from disc web to trunnion support end section. Wheel rim outer surface is made composing internal circuit flow section axial section with axial length equal to rim generatrix projection on rotor shaft axis, and with radius increasing in LPC axial cross-section towards working fluid flow, wherein rim is connected with disc web to make front and rear circular conical flanges. Rear flange is provided with annular element made for for subsequent permanent connection with second stage disc web front flange, and grooves are uniformly spaced apart along wheel rim perimeter with angular frequency Y=(4.6÷6.2) [unit/rad] and are made with mutually inclined side edges, having in cross section configuration of lock joint with blade root element. Slots for fitting blade roots are uniformly spaced apart along disc rim perimeter, wherein each slot foot is located in plane parallel to rotor shaft axis, and groove bottom longitudinal axis makes with rotor shaft axis in projection on said plane angle of α blade shank installation, defined in range of values α=(16÷22)°, and root inlet and outlet edges are made diverging to peripheral blade end with gradient Gtheir connecting chord increase, equal to G=(L-L)/H=(9.3÷13.3)·10[m/m], where Lis peripheral chord length connecting blade body inlet and outlet edges in conditional plane perpendicular to blade body axis; Lis same, root chord length; His blade body average height.EFFECT: invention allows to increase efficiency and increase gas-dynamic stability margin at all operation modes of compressor while increasing LPC rotor impeller service life without increase of material consumption.19 cl, 5 dwg
Изобретение относится к области авиадвигателестроения. Рабочее колесо первой ступени ротора, включающего вал барабанно-дисковой конструкции компрессора низкого давления (КНД) турбореактивного двигателя (ТРД) содержит диск, наделенный пазами, и лопаточный венец, при этом диск выполнен в виде моноэлемента, включающего ступицу с центральным отверстием, полотно и обод, а лопатки содержат каждая хвостовик и перо с профилем, образованным вогнутым корытом и выпуклой спинкой, сопряженными входной и выходной кромками. Полотно диска выполнено с переменным по высоте сечением, конически сужающимся от ступицы к ободу с градиентом Gуменьшения толщины в указанном направлении, равнымG=(δ- δ)/Н=(0,11÷0,15) [м/м],где δ- толщина периферийной части полотна диска; δ- толщина прикорневой части полотна; Н- радиальная высота полотна диска между участками сопряжений со ступицей и ободом. Ступица выполнена как одно целое с цапфой передней опоры вала ротора, односторонне развитой ко входу в КНД и выполненной с переменным диаметром, ступенчато уменьшающимся не менее чем через два уступа от полотна диска к опорному концевому участку цапфы. Внешняя поверхность обода диска выполнена составляющей осевой участок внутреннего контура проточной части с осевой длиной, равной проекции образующей обода на ось вала ротора, и с радиусом, возрастающим в осевом сечении КНД в сторону потока рабочего тела, причем обод соединен с полотном диска с образованием фронтальной и тыльной кольцевых конических полок. Тыльная полка снабжена кольцевым элементом, выполненным для последующего неразъемного соединения с фронтальной полкой полотна диска второй ступени, а пазы равномерно разнесены</description><language>eng ; rus</language><subject>BLASTING ; CHEMICAL OR PHYSICAL PROCESSES, e.g. CATALYSIS OR COLLOIDCHEMISTRY ; ENGINE PLANTS IN GENERAL ; HEATING ; LIGHTING ; MACHINES OR ENGINES IN GENERAL ; MECHANICAL ENGINEERING ; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES ; PERFORMING OPERATIONS ; PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL ; STEAM ENGINES ; THEIR RELEVANT APPARATUS ; TRANSPORTING ; WEAPONS</subject><creationdate>2016</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=20161127&DB=EPODOC&CC=RU&NR=2603382C1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,309,781,886,25569,76552</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20161127&DB=EPODOC&CC=RU&NR=2603382C1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Erichev Dmitrij JUrevich</creatorcontrib><creatorcontrib>Marchukov Evgenij JUvenalevich</creatorcontrib><creatorcontrib>Artjukhov Aleksandr Viktorovich</creatorcontrib><creatorcontrib>Poljakov Konstantin Sergeevich</creatorcontrib><creatorcontrib>Uzbekov Andrej Valerevich</creatorcontrib><creatorcontrib>Manapov Irik Usmanovich</creatorcontrib><creatorcontrib>Kuznetsov Igor Sergeevich</creatorcontrib><title>TURBOJET ENGINE LOW-PRESSURE COMPRESSOR FIRST STAGE ROTOR IMPELLER (VERSIONS)</title><description>FIELD: engines and pumps.SUBSTANCE: invention relates to engine building. Rotor first stage impeller, including jet turbine engine (JTE) low pressure compressor (LPC) drum-disc design shaft comprises disc equipped with slots, and blade ring, wherein disc is made in form of one-piece element including hub with central hole, web and rim, and blades each contain tail and wing with profile formed by concave pressure side and convex back, coupled by inlet and outlet edges. Disc web is made with variable in height section, conically narrowing from hub to rim with gradient of Gthickness reducing in specified direction, equal to G=(δ-δ)/H=(0.11÷0.15) [m/m], where δis disc web peripheral part thickness; δis web root part thickness; His disc web radial height between sections of connections with hub and rim. Hub is made integral with rotor shaft front bearing trunnion developed on one side to LPC inlet and made with variable diameter, gradually decreasing at least in two projections from disc web to trunnion support end section. Wheel rim outer surface is made composing internal circuit flow section axial section with axial length equal to rim generatrix projection on rotor shaft axis, and with radius increasing in LPC axial cross-section towards working fluid flow, wherein rim is connected with disc web to make front and rear circular conical flanges. Rear flange is provided with annular element made for for subsequent permanent connection with second stage disc web front flange, and grooves are uniformly spaced apart along wheel rim perimeter with angular frequency Y=(4.6÷6.2) [unit/rad] and are made with mutually inclined side edges, having in cross section configuration of lock joint with blade root element. Slots for fitting blade roots are uniformly spaced apart along disc rim perimeter, wherein each slot foot is located in plane parallel to rotor shaft axis, and groove bottom longitudinal axis makes with rotor shaft axis in projection on said plane angle of α blade shank installation, defined in range of values α=(16÷22)°, and root inlet and outlet edges are made diverging to peripheral blade end with gradient Gtheir connecting chord increase, equal to G=(L-L)/H=(9.3÷13.3)·10[m/m], where Lis peripheral chord length connecting blade body inlet and outlet edges in conditional plane perpendicular to blade body axis; Lis same, root chord length; His blade body average height.EFFECT: invention allows to increase efficiency and increase gas-dynamic stability margin at all operation modes of compressor while increasing LPC rotor impeller service life without increase of material consumption.19 cl, 5 dwg
Изобретение относится к области авиадвигателестроения. Рабочее колесо первой ступени ротора, включающего вал барабанно-дисковой конструкции компрессора низкого давления (КНД) турбореактивного двигателя (ТРД) содержит диск, наделенный пазами, и лопаточный венец, при этом диск выполнен в виде моноэлемента, включающего ступицу с центральным отверстием, полотно и обод, а лопатки содержат каждая хвостовик и перо с профилем, образованным вогнутым корытом и выпуклой спинкой, сопряженными входной и выходной кромками. Полотно диска выполнено с переменным по высоте сечением, конически сужающимся от ступицы к ободу с градиентом Gуменьшения толщины в указанном направлении, равнымG=(δ- δ)/Н=(0,11÷0,15) [м/м],где δ- толщина периферийной части полотна диска; δ- толщина прикорневой части полотна; Н- радиальная высота полотна диска между участками сопряжений со ступицей и ободом. Ступица выполнена как одно целое с цапфой передней опоры вала ротора, односторонне развитой ко входу в КНД и выполненной с переменным диаметром, ступенчато уменьшающимся не менее чем через два уступа от полотна диска к опорному концевому участку цапфы. Внешняя поверхность обода диска выполнена составляющей осевой участок внутреннего контура проточной части с осевой длиной, равной проекции образующей обода на ось вала ротора, и с радиусом, возрастающим в осевом сечении КНД в сторону потока рабочего тела, причем обод соединен с полотном диска с образованием фронтальной и тыльной кольцевых конических полок. Тыльная полка снабжена кольцевым элементом, выполненным для последующего неразъемного соединения с фронтальной полкой полотна диска второй ступени, а пазы равномерно разнесены</description><subject>BLASTING</subject><subject>CHEMICAL OR PHYSICAL PROCESSES, e.g. CATALYSIS OR COLLOIDCHEMISTRY</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>PERFORMING OPERATIONS</subject><subject>PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL</subject><subject>STEAM ENGINES</subject><subject>THEIR RELEVANT APPARATUS</subject><subject>TRANSPORTING</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2016</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZPANCQ1y8vdyDVFw9XP39HNV8PEP1w0Icg0ODg1yVXD29wWz_YMU3DyDgkMUgkMc3V0VgvxDgCKevgGuPj6uQQoaYa5BwZ7-fsGaPAysaYk5xam8UJqbQcHNNcTZQze1ID8-tbggMTk1L7UkPijUyMzA2NjCyNnQmAglANe3LnQ</recordid><startdate>20161127</startdate><enddate>20161127</enddate><creator>Erichev Dmitrij JUrevich</creator><creator>Marchukov Evgenij JUvenalevich</creator><creator>Artjukhov Aleksandr Viktorovich</creator><creator>Poljakov Konstantin Sergeevich</creator><creator>Uzbekov Andrej Valerevich</creator><creator>Manapov Irik Usmanovich</creator><creator>Kuznetsov Igor Sergeevich</creator><scope>EVB</scope></search><sort><creationdate>20161127</creationdate><title>TURBOJET ENGINE LOW-PRESSURE COMPRESSOR FIRST STAGE ROTOR IMPELLER (VERSIONS)</title><author>Erichev Dmitrij JUrevich ; Marchukov Evgenij JUvenalevich ; Artjukhov Aleksandr Viktorovich ; Poljakov Konstantin Sergeevich ; Uzbekov Andrej Valerevich ; Manapov Irik Usmanovich ; Kuznetsov Igor Sergeevich</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_RU2603382C13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; rus</language><creationdate>2016</creationdate><topic>BLASTING</topic><topic>CHEMICAL OR PHYSICAL PROCESSES, e.g. CATALYSIS OR COLLOIDCHEMISTRY</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>PERFORMING OPERATIONS</topic><topic>PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL</topic><topic>STEAM ENGINES</topic><topic>THEIR RELEVANT APPARATUS</topic><topic>TRANSPORTING</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>Erichev Dmitrij JUrevich</creatorcontrib><creatorcontrib>Marchukov Evgenij JUvenalevich</creatorcontrib><creatorcontrib>Artjukhov Aleksandr Viktorovich</creatorcontrib><creatorcontrib>Poljakov Konstantin Sergeevich</creatorcontrib><creatorcontrib>Uzbekov Andrej Valerevich</creatorcontrib><creatorcontrib>Manapov Irik Usmanovich</creatorcontrib><creatorcontrib>Kuznetsov Igor Sergeevich</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Erichev Dmitrij JUrevich</au><au>Marchukov Evgenij JUvenalevich</au><au>Artjukhov Aleksandr Viktorovich</au><au>Poljakov Konstantin Sergeevich</au><au>Uzbekov Andrej Valerevich</au><au>Manapov Irik Usmanovich</au><au>Kuznetsov Igor Sergeevich</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>TURBOJET ENGINE LOW-PRESSURE COMPRESSOR FIRST STAGE ROTOR IMPELLER (VERSIONS)</title><date>2016-11-27</date><risdate>2016</risdate><abstract>FIELD: engines and pumps.SUBSTANCE: invention relates to engine building. Rotor first stage impeller, including jet turbine engine (JTE) low pressure compressor (LPC) drum-disc design shaft comprises disc equipped with slots, and blade ring, wherein disc is made in form of one-piece element including hub with central hole, web and rim, and blades each contain tail and wing with profile formed by concave pressure side and convex back, coupled by inlet and outlet edges. Disc web is made with variable in height section, conically narrowing from hub to rim with gradient of Gthickness reducing in specified direction, equal to G=(δ-δ)/H=(0.11÷0.15) [m/m], where δis disc web peripheral part thickness; δis web root part thickness; His disc web radial height between sections of connections with hub and rim. Hub is made integral with rotor shaft front bearing trunnion developed on one side to LPC inlet and made with variable diameter, gradually decreasing at least in two projections from disc web to trunnion support end section. Wheel rim outer surface is made composing internal circuit flow section axial section with axial length equal to rim generatrix projection on rotor shaft axis, and with radius increasing in LPC axial cross-section towards working fluid flow, wherein rim is connected with disc web to make front and rear circular conical flanges. Rear flange is provided with annular element made for for subsequent permanent connection with second stage disc web front flange, and grooves are uniformly spaced apart along wheel rim perimeter with angular frequency Y=(4.6÷6.2) [unit/rad] and are made with mutually inclined side edges, having in cross section configuration of lock joint with blade root element. Slots for fitting blade roots are uniformly spaced apart along disc rim perimeter, wherein each slot foot is located in plane parallel to rotor shaft axis, and groove bottom longitudinal axis makes with rotor shaft axis in projection on said plane angle of α blade shank installation, defined in range of values α=(16÷22)°, and root inlet and outlet edges are made diverging to peripheral blade end with gradient Gtheir connecting chord increase, equal to G=(L-L)/H=(9.3÷13.3)·10[m/m], where Lis peripheral chord length connecting blade body inlet and outlet edges in conditional plane perpendicular to blade body axis; Lis same, root chord length; His blade body average height.EFFECT: invention allows to increase efficiency and increase gas-dynamic stability margin at all operation modes of compressor while increasing LPC rotor impeller service life without increase of material consumption.19 cl, 5 dwg
Изобретение относится к области авиадвигателестроения. Рабочее колесо первой ступени ротора, включающего вал барабанно-дисковой конструкции компрессора низкого давления (КНД) турбореактивного двигателя (ТРД) содержит диск, наделенный пазами, и лопаточный венец, при этом диск выполнен в виде моноэлемента, включающего ступицу с центральным отверстием, полотно и обод, а лопатки содержат каждая хвостовик и перо с профилем, образованным вогнутым корытом и выпуклой спинкой, сопряженными входной и выходной кромками. Полотно диска выполнено с переменным по высоте сечением, конически сужающимся от ступицы к ободу с градиентом Gуменьшения толщины в указанном направлении, равнымG=(δ- δ)/Н=(0,11÷0,15) [м/м],где δ- толщина периферийной части полотна диска; δ- толщина прикорневой части полотна; Н- радиальная высота полотна диска между участками сопряжений со ступицей и ободом. Ступица выполнена как одно целое с цапфой передней опоры вала ротора, односторонне развитой ко входу в КНД и выполненной с переменным диаметром, ступенчато уменьшающимся не менее чем через два уступа от полотна диска к опорному концевому участку цапфы. Внешняя поверхность обода диска выполнена составляющей осевой участок внутреннего контура проточной части с осевой длиной, равной проекции образующей обода на ось вала ротора, и с радиусом, возрастающим в осевом сечении КНД в сторону потока рабочего тела, причем обод соединен с полотном диска с образованием фронтальной и тыльной кольцевых конических полок. Тыльная полка снабжена кольцевым элементом, выполненным для последующего неразъемного соединения с фронтальной полкой полотна диска второй ступени, а пазы равномерно разнесены</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | BLASTING CHEMICAL OR PHYSICAL PROCESSES, e.g. CATALYSIS OR COLLOIDCHEMISTRY ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PERFORMING OPERATIONS PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL STEAM ENGINES THEIR RELEVANT APPARATUS TRANSPORTING WEAPONS |
| title | TURBOJET ENGINE LOW-PRESSURE COMPRESSOR FIRST STAGE ROTOR IMPELLER (VERSIONS) |
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