RU2012109596A - METHOD FOR REDUCING DYNAMIC STRESSES IN WORKING BLADES OF THE LAST TURBINE STAGE - Google Patents

METHOD FOR REDUCING DYNAMIC STRESSES IN WORKING BLADES OF THE LAST TURBINE STAGE Download PDF

Info

Publication number
RU2012109596A
RU2012109596A RU2012109596/06A RU2012109596A RU2012109596A RU 2012109596 A RU2012109596 A RU 2012109596A RU 2012109596/06 A RU2012109596/06 A RU 2012109596/06A RU 2012109596 A RU2012109596 A RU 2012109596A RU 2012109596 A RU2012109596 A RU 2012109596A
Authority
RU
Russia
Prior art keywords
turbine
last stage
dynamic stresses
reducing dynamic
blade
Prior art date
Application number
RU2012109596/06A
Other languages
Russian (ru)
Other versions
RU2499889C1 (en
Inventor
Мидхат Губайдуллович Хабибуллин
Владимир Фёдорович Иванников
Михаил Викторович Додонов
Евгений Геннадьевич Чирков
Вячеслав Хазиевич Хуснуллин
Фарит Кавиевич Закиев
Original Assignee
Открытое акционерное общество Конструкторско-производственное предприятие "Авиамотор"
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Открытое акционерное общество Конструкторско-производственное предприятие "Авиамотор" filed Critical Открытое акционерное общество Конструкторско-производственное предприятие "Авиамотор"
Priority to RU2012109596/06A priority Critical patent/RU2499889C1/en
Publication of RU2012109596A publication Critical patent/RU2012109596A/en
Application granted granted Critical
Publication of RU2499889C1 publication Critical patent/RU2499889C1/en

Links

Abstract

Способ снижения динамических напряжений в рабочих лопатках последней ступени силовой турбины, содержащей рабочие колеса, размещенные в статоре, отличающийся тем, что при угле раскрытия проточной части в меридиональном сечении в пределах 13…23° и соответственно отношении среднего диаметра рабочего колеса последней ступени силовой турбины к высоте рабочей лопатки на выходе из турбины от 3,5 до 4,0, минимальную толщину полотна диска последней ступени турбины выбирают равной или большей, чем ширина пера рабочей лопатки последней ступени силовой турбины в корневом сечении.A method of reducing dynamic stresses in the rotor blades of the last stage of a power turbine containing impellers located in the stator, characterized in that when the opening angle of the flow part in the meridional section is within 13 ... 23 ° and, accordingly, the ratio of the average diameter of the impeller of the last stage of the power turbine is the height of the working blade at the outlet of the turbine is from 3.5 to 4.0, the minimum thickness of the blade web of the disk of the last stage of the turbine is chosen equal to or greater than the width of the pen of the working blade of the last stage of the force th root of the turbine section.

Claims (1)

Способ снижения динамических напряжений в рабочих лопатках последней ступени силовой турбины, содержащей рабочие колеса, размещенные в статоре, отличающийся тем, что при угле раскрытия проточной части в меридиональном сечении в пределах 13…23° и соответственно отношении среднего диаметра рабочего колеса последней ступени силовой турбины к высоте рабочей лопатки на выходе из турбины от 3,5 до 4,0, минимальную толщину полотна диска последней ступени турбины выбирают равной или большей, чем ширина пера рабочей лопатки последней ступени силовой турбины в корневом сечении. A method of reducing dynamic stresses in the rotor blades of the last stage of a power turbine containing impellers located in the stator, characterized in that when the opening angle of the flow part in the meridional section is within 13 ... 23 ° and, accordingly, the ratio of the average diameter of the impeller of the last stage of the power turbine is the height of the working blade at the outlet of the turbine is from 3.5 to 4.0, the minimum thickness of the blade web of the disk of the last stage of the turbine is chosen equal to or greater than the width of the pen of the working blade of the last stage of the force th root of the turbine section.
RU2012109596/06A 2012-03-13 2012-03-13 Reduction method of dynamic stresses in rotating blades of turbine last stage RU2499889C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2012109596/06A RU2499889C1 (en) 2012-03-13 2012-03-13 Reduction method of dynamic stresses in rotating blades of turbine last stage

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2012109596/06A RU2499889C1 (en) 2012-03-13 2012-03-13 Reduction method of dynamic stresses in rotating blades of turbine last stage

Publications (2)

Publication Number Publication Date
RU2012109596A true RU2012109596A (en) 2013-09-20
RU2499889C1 RU2499889C1 (en) 2013-11-27

Family

ID=49182953

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2012109596/06A RU2499889C1 (en) 2012-03-13 2012-03-13 Reduction method of dynamic stresses in rotating blades of turbine last stage

Country Status (1)

Country Link
RU (1) RU2499889C1 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2703844C1 (en) * 2018-10-04 2019-10-22 Акционерное общество "РОТЕК" (АО "РОТЕК") Method for evaluation of residual life of the first stage of gas turbine plant

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6375428B1 (en) * 2000-08-10 2002-04-23 The Boeing Company Turbine blisk rim friction finger damper
FR2824597B1 (en) * 2001-05-11 2004-04-02 Snecma Moteurs REDUCTION OF VIBRATION IN A STRUCTURE COMPRISING A ROTOR AND FIXED DISTURBANCE SOURCES
FR2866057B1 (en) * 2004-02-06 2006-04-28 Snecma Moteurs DEVICE FOR BALANCING A ROTOR DISC, DISC EQUIPPED WITH SUCH A DEVICE, AND ROTOR HAVING SUCH A DISK
DE102009033618A1 (en) * 2009-07-17 2011-01-20 Mtu Aero Engines Gmbh Method for frequency detuning of rotor body of rotor of gas turbine, involves providing rotor raw body that is made of base material
RU99066U1 (en) * 2010-07-15 2010-11-10 Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации Минпромторг России AXIAL MULTI-STAGE TURBO MACHINE ROTOR

Also Published As

Publication number Publication date
RU2499889C1 (en) 2013-11-27

Similar Documents

Publication Publication Date Title
NZ701728A (en) Rotor blade for a wind power plant
RU2014135419A (en) TURBOJET FAN BLADE
GB2457412B (en) Tidal electricity generating apparatus
JP2014533809A5 (en)
EP2843239A3 (en) Fan and impeller thereof
IN2014DN09485A (en)
EP2762724A3 (en) Ultrasonic sound emitting devices for wind turbines
WO2009101596A3 (en) Shrouded turbine blade design
MX2019005981A (en) Multiple-blade wind machine with shrouded rotors.
EP2685065A3 (en) A gas turbine engine
PL410832A1 (en) Wind turbine, wind farm and method for generating energy
IN2014DE01617A (en)
EP2562427A3 (en) A rotor for a compressor of a gas turbine
FR2931871B1 (en) BLOWER ROTOR FOR A TURBOMACHINE.
MX355112B (en) Windturbine and building having such a wind turbine.
MX2016005523A (en) Centrifugal compressor impeller with blades having an s-shaped trailing edge.
MX2017011693A (en) Improved wind turbine suitable for mounting without a wind turbine tower.
NZ732950A (en) A blade for a vertical axis turbine, a turbine comprising the blade and a method of operation of the turbine
WO2013064674A3 (en) Turbomachine
GB201210287D0 (en) Vertical axis wind turbine
RU2015128801A (en) HYDRAULIC TURBINE
GB201204339D0 (en) A wind turbine assembly
GB2492732A (en) A turbine blade assembly
RU2012109596A (en) METHOD FOR REDUCING DYNAMIC STRESSES IN WORKING BLADES OF THE LAST TURBINE STAGE
RU2015150305A (en) COMPRESSOR OPERATING WHEEL

Legal Events

Date Code Title Description
MM4A The patent is invalid due to non-payment of fees

Effective date: 20140314