MULTISTAGE GAS TURBINE
FIELD: multistage gas turbine of aircraft and ground application. ^ SUBSTANCE: according to invention, in multistage gas turbine with higher pressure relief chamber at outlet limited over periphery by labyrinth seal, said seal is made multistage, air space between first and second side from relief c...
Gespeichert in:
Hauptverfasser: | , , , , , |
---|---|
Format: | Patent |
Sprache: | eng ; rus |
Schlagworte: | |
Online-Zugang: | Volltext bestellen |
Tags: |
Tag hinzufügen
Keine Tags, Fügen Sie den ersten Tag hinzu!
|
container_end_page | |
---|---|
container_issue | |
container_start_page | |
container_title | |
container_volume | |
creator | JAZEV V.M SYCHEV V.K LATYSHEV V.G KUZNETSOV V.A BELKANOV V.A FADEEV S.I |
description | FIELD: multistage gas turbine of aircraft and ground application. ^ SUBSTANCE: according to invention, in multistage gas turbine with higher pressure relief chamber at outlet limited over periphery by labyrinth seal, said seal is made multistage, air space between first and second side from relief chamber stages of labyrinth seal is connected with gas chamber before last disk of turbine by channels made under feed of locks of working blades of last stage and slot spaces between ring flange on rim of disk of last stage and rim of disk from side of inlet in direction of gas flow at F1/F2=3...10 where F1 is passage area of first stage of labyrinth seal, and F2 is area of slot spaces. ^ EFFECT: improved reliability of multistage gas turbine owing to provision of effective cooling of last stage disk rim and disk-to-working blade lock joint. ^ 2 dwg |
format | Patent |
fullrecord | <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_RU2263809C2</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>RU2263809C2</sourcerecordid><originalsourceid>FETCH-epo_espacenet_RU2263809C23</originalsourceid><addsrcrecordid>eNrjZBDzDfUJ8QwOcXR3VXB3DFYICQ1y8vRz5WFgTUvMKU7lhdLcDApuriHOHrqpBfnxqcUFicmpeakl8UGhRkZmxhYGls5GxkQoAQCF8x7-</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>MULTISTAGE GAS TURBINE</title><source>esp@cenet</source><creator>JAZEV V.M ; SYCHEV V.K ; LATYSHEV V.G ; KUZNETSOV V.A ; BELKANOV V.A ; FADEEV S.I</creator><creatorcontrib>JAZEV V.M ; SYCHEV V.K ; LATYSHEV V.G ; KUZNETSOV V.A ; BELKANOV V.A ; FADEEV S.I</creatorcontrib><description>FIELD: multistage gas turbine of aircraft and ground application. ^ SUBSTANCE: according to invention, in multistage gas turbine with higher pressure relief chamber at outlet limited over periphery by labyrinth seal, said seal is made multistage, air space between first and second side from relief chamber stages of labyrinth seal is connected with gas chamber before last disk of turbine by channels made under feed of locks of working blades of last stage and slot spaces between ring flange on rim of disk of last stage and rim of disk from side of inlet in direction of gas flow at F1/F2=3...10 where F1 is passage area of first stage of labyrinth seal, and F2 is area of slot spaces. ^ EFFECT: improved reliability of multistage gas turbine owing to provision of effective cooling of last stage disk rim and disk-to-working blade lock joint. ^ 2 dwg</description><edition>7</edition><language>eng ; rus</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 ; STEAM ENGINES ; WEAPONS</subject><creationdate>2005</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=20051110&DB=EPODOC&CC=RU&NR=2263809C2$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25563,76418</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20051110&DB=EPODOC&CC=RU&NR=2263809C2$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>JAZEV V.M</creatorcontrib><creatorcontrib>SYCHEV V.K</creatorcontrib><creatorcontrib>LATYSHEV V.G</creatorcontrib><creatorcontrib>KUZNETSOV V.A</creatorcontrib><creatorcontrib>BELKANOV V.A</creatorcontrib><creatorcontrib>FADEEV S.I</creatorcontrib><title>MULTISTAGE GAS TURBINE</title><description>FIELD: multistage gas turbine of aircraft and ground application. ^ SUBSTANCE: according to invention, in multistage gas turbine with higher pressure relief chamber at outlet limited over periphery by labyrinth seal, said seal is made multistage, air space between first and second side from relief chamber stages of labyrinth seal is connected with gas chamber before last disk of turbine by channels made under feed of locks of working blades of last stage and slot spaces between ring flange on rim of disk of last stage and rim of disk from side of inlet in direction of gas flow at F1/F2=3...10 where F1 is passage area of first stage of labyrinth seal, and F2 is area of slot spaces. ^ EFFECT: improved reliability of multistage gas turbine owing to provision of effective cooling of last stage disk rim and disk-to-working blade lock joint. ^ 2 dwg</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>STEAM ENGINES</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2005</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZBDzDfUJ8QwOcXR3VXB3DFYICQ1y8vRz5WFgTUvMKU7lhdLcDApuriHOHrqpBfnxqcUFicmpeakl8UGhRkZmxhYGls5GxkQoAQCF8x7-</recordid><startdate>20051110</startdate><enddate>20051110</enddate><creator>JAZEV V.M</creator><creator>SYCHEV V.K</creator><creator>LATYSHEV V.G</creator><creator>KUZNETSOV V.A</creator><creator>BELKANOV V.A</creator><creator>FADEEV S.I</creator><scope>EVB</scope></search><sort><creationdate>20051110</creationdate><title>MULTISTAGE GAS TURBINE</title><author>JAZEV V.M ; SYCHEV V.K ; LATYSHEV V.G ; KUZNETSOV V.A ; BELKANOV V.A ; FADEEV S.I</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_RU2263809C23</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; rus</language><creationdate>2005</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>STEAM ENGINES</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>JAZEV V.M</creatorcontrib><creatorcontrib>SYCHEV V.K</creatorcontrib><creatorcontrib>LATYSHEV V.G</creatorcontrib><creatorcontrib>KUZNETSOV V.A</creatorcontrib><creatorcontrib>BELKANOV V.A</creatorcontrib><creatorcontrib>FADEEV S.I</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>JAZEV V.M</au><au>SYCHEV V.K</au><au>LATYSHEV V.G</au><au>KUZNETSOV V.A</au><au>BELKANOV V.A</au><au>FADEEV S.I</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>MULTISTAGE GAS TURBINE</title><date>2005-11-10</date><risdate>2005</risdate><abstract>FIELD: multistage gas turbine of aircraft and ground application. ^ SUBSTANCE: according to invention, in multistage gas turbine with higher pressure relief chamber at outlet limited over periphery by labyrinth seal, said seal is made multistage, air space between first and second side from relief chamber stages of labyrinth seal is connected with gas chamber before last disk of turbine by channels made under feed of locks of working blades of last stage and slot spaces between ring flange on rim of disk of last stage and rim of disk from side of inlet in direction of gas flow at F1/F2=3...10 where F1 is passage area of first stage of labyrinth seal, and F2 is area of slot spaces. ^ EFFECT: improved reliability of multistage gas turbine owing to provision of effective cooling of last stage disk rim and disk-to-working blade lock joint. ^ 2 dwg</abstract><edition>7</edition><oa>free_for_read</oa></addata></record> |
fulltext | fulltext_linktorsrc |
identifier | |
ispartof | |
issn | |
language | eng ; rus |
recordid | cdi_epo_espacenet_RU2263809C2 |
source | esp@cenet |
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 STEAM ENGINES WEAPONS |
title | MULTISTAGE GAS TURBINE |
url | https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2025-01-08T06%3A56%3A45IST&url_ver=Z39.88-2004&url_ctx_fmt=infofi/fmt:kev:mtx:ctx&rfr_id=info:sid/primo.exlibrisgroup.com:primo3-Article-epo_EVB&rft_val_fmt=info:ofi/fmt:kev:mtx:patent&rft.genre=patent&rft.au=JAZEV%20V.M&rft.date=2005-11-10&rft_id=info:doi/&rft_dat=%3Cepo_EVB%3ERU2263809C2%3C/epo_EVB%3E%3Curl%3E%3C/url%3E&disable_directlink=true&sfx.directlink=off&sfx.report_link=0&rft_id=info:oai/&rft_id=info:pmid/&rfr_iscdi=true |