RU2006112375A - METHOD FOR DIAGNOSTIC OF UNSTABLE OPERATION OF THE COMPRESSOR OF THE GAS TURBINE ENGINE ON START-UP - Google Patents

METHOD FOR DIAGNOSTIC OF UNSTABLE OPERATION OF THE COMPRESSOR OF THE GAS TURBINE ENGINE ON START-UP Download PDF

Info

Publication number
RU2006112375A
RU2006112375A RU2006112375/06A RU2006112375A RU2006112375A RU 2006112375 A RU2006112375 A RU 2006112375A RU 2006112375/06 A RU2006112375/06 A RU 2006112375/06A RU 2006112375 A RU2006112375 A RU 2006112375A RU 2006112375 A RU2006112375 A RU 2006112375A
Authority
RU
Russia
Prior art keywords
compressor
parameter
tnd
low
turbine engine
Prior art date
Application number
RU2006112375/06A
Other languages
Russian (ru)
Other versions
RU2316678C1 (en
Inventor
Валерий Георгиевич Ипполитов (RU)
Валерий Георгиевич Ипполитов
х Антон Иванович Полул (RU)
Антон Иванович Полулях
Юрий Семенович Савенков (RU)
Юрий Семенович Савенков
Алексей Николаевич Саженков (RU)
Алексей Николаевич Саженков
Юрий Абрамович Трубников (RU)
Юрий Абрамович Трубников
Original Assignee
Открытое акционерное общество "Авиадвигатель" (RU)
Открытое акционерное общество "Авиадвигатель"
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 "Авиадвигатель" (RU), Открытое акционерное общество "Авиадвигатель" filed Critical Открытое акционерное общество "Авиадвигатель" (RU)
Priority to RU2006112375/06A priority Critical patent/RU2316678C1/en
Publication of RU2006112375A publication Critical patent/RU2006112375A/en
Application granted granted Critical
Publication of RU2316678C1 publication Critical patent/RU2316678C1/en

Links

Landscapes

  • Control Of Positive-Displacement Air Blowers (AREA)
  • Control Of Turbines (AREA)
  • Testing Of Engines (AREA)

Claims (4)

1. Способ диагностики неустойчивой работы компрессора газотурбинного двигателя на запуске, включающий измерение температуры газов за турбиной низкого давления Ттнд, частоты вращения ротора высокого давления nвд, определение первой производной по времени параметра
Figure 00000001
и параметра
Figure 00000002
отличающийся тем, что дополнительно определяют отношение первой производной параметра Ттнд к первой производной параметра nвд, т.е.
Figure 00000003
на основе заранее установленных запасов газодинамической устойчивости компрессора на запуске формируют предельно допустимое значение
Figure 00000004
сравнивают
Figure 00000005
с
Figure 00000006
и при
Figure 00000007
формируют логический сигнал I о срыве компрессора.1. A method for diagnosing unstable operation of a compressor of a gas turbine engine at start-up, including measuring the temperature of gases behind a low-pressure turbine T tnd , high-pressure rotor speed n vd , determining the first time derivative of the parameter
Figure 00000001
and parameter
Figure 00000002
characterized in that it further determines the ratio of the first derivative of the parameter T tnd to the first derivative of the parameter n vd , i.e.
Figure 00000003
on the basis of pre-established reserves of gas-dynamic stability of the compressor at the start, the maximum permissible value is formed
Figure 00000004
compare
Figure 00000005
from
Figure 00000006
and with
Figure 00000007
form a logical signal I about the failure of the compressor. 2. Способ по п.1, отличающийся тем, что сравнение
Figure 00000008
с
Figure 00000009
осуществляют при изменении частоты вращения nвд от 20 до 38%.2. The method according to claim 1, characterized in that the comparison
Figure 00000008
from
Figure 00000009
carry out when changing the speed n vd from 20 to 38%. 3. Способ по п.1, отличающийся тем, что измерение температуры газов за турбиной низкого давления Ттнд осуществляют малоинерционной хромель-алюмелевой термопарой с открытым горячим спаем.3. The method according to claim 1, characterized in that the temperature measurement of the gases behind the low-pressure turbine T tnd is carried out by a low-inertia chromel-alumel thermocouple with an open hot junction. 4. Способ по п.1, отличающийся тем, что в качестве предельно допустимого значения
Figure 00000009
используют числовое значение 50 [°С/%].4. The method according to claim 1, characterized in that as the maximum permissible value
Figure 00000009
use a numerical value of 50 [° C /%].
RU2006112375/06A 2006-04-13 2006-04-13 Method of diagnosing unstable operation of gas-turbine engine compressor at starting RU2316678C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2006112375/06A RU2316678C1 (en) 2006-04-13 2006-04-13 Method of diagnosing unstable operation of gas-turbine engine compressor at starting

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2006112375/06A RU2316678C1 (en) 2006-04-13 2006-04-13 Method of diagnosing unstable operation of gas-turbine engine compressor at starting

Publications (2)

Publication Number Publication Date
RU2006112375A true RU2006112375A (en) 2007-10-20
RU2316678C1 RU2316678C1 (en) 2008-02-10

Family

ID=38925133

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2006112375/06A RU2316678C1 (en) 2006-04-13 2006-04-13 Method of diagnosing unstable operation of gas-turbine engine compressor at starting

Country Status (1)

Country Link
RU (1) RU2316678C1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103216461A (en) * 2013-04-17 2013-07-24 南京航空航天大学 Stall inception identification method of axial-flow compressor

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2964087B1 (en) * 2010-08-25 2013-06-14 Turbomeca METHOD FOR OPTIMIZING THE ENGINE OPERABILITY OF AN AIRCRAFT AND INDEPENDENT POWER UNIT FOR IMPLEMENTING THE SAME
RU2747542C1 (en) * 2020-09-10 2021-05-06 Акционерное общество"ОДК-Авиадвигатель" Method for protecting a gas turbine engine from pumping

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103216461A (en) * 2013-04-17 2013-07-24 南京航空航天大学 Stall inception identification method of axial-flow compressor
CN103216461B (en) * 2013-04-17 2016-01-13 南京航空航天大学 The stall inception identification method of axial-flow compressor

Also Published As

Publication number Publication date
RU2316678C1 (en) 2008-02-10

Similar Documents

Publication Publication Date Title
CN102539162B (en) The method and system of compressor health monitoring
US20140007591A1 (en) Advanced tip-timing measurement blade mode identification
CN105593490B (en) The control device of turbocharger
US11293353B2 (en) Transient control to extend part life in gas turbine engine
SE0502822L (en) Method and apparatus for monitoring the function of a sensor or system
EP1811133A3 (en) Sensor diagnostics using a quality parameter model
RU2006143730A (en) METHOD FOR GAS-TURBINE ENGINE CONTROL IN DYNAMIC ACCELERATION AND THROTTLE MODES
US20150075265A1 (en) Measurement device and method for evaluating turbomachine clearances
US10018122B2 (en) Pressure sensor noise filter prior to surge detection for a gas turbine engine
RU2006112375A (en) METHOD FOR DIAGNOSTIC OF UNSTABLE OPERATION OF THE COMPRESSOR OF THE GAS TURBINE ENGINE ON START-UP
RU2008119292A (en) METHOD FOR DIAGNOSIS OF COMPRESSOR DISTURBANCE
EP1837506A3 (en) Monitoring gas turbine engines
RU2008103208A (en) METHOD FOR GAS-TURBINE ENGINE CONTROL
BR102013027800A2 (en) METHOD FOR RECOGNIZING FUEL TYPE EFFECTIVELY USED IN AN INTERNAL COMBUSTION ENGINE
EP2713015A2 (en) Turbomachine including a pressure sensing system
RU2003134681A (en) METHOD FOR PROTECTING A COMPRESSOR IN UNSTABLE OPERATION OF A GAS TURBINE ENGINE
RU2527850C1 (en) Method of control over gas turbine engine compressor actuators
RU2012134362A (en) METHOD FOR DIAGNOSTIC OF TECHNICAL CONDITION OF AIRCRAFT GAS TURBINE ENGINES
RU2009112237A (en) METHOD FOR CONTROLING THE TECHNICAL CONDITION OF A GAS-TURBINE INSTALLATION
RU2006100531A (en) METHOD FOR PROTECTING A GAS TURBINE ENGINE FROM THE ORIGIN OF UNSTABLE COMPRESSOR OPERATION
RU2668310C1 (en) Method for determining gas temperature in front of turbine in afterburner mode of turbojet engine
RU2005132735A (en) METHOD FOR EMERGENCY PROTECTION OF A GAS-TURBINE ENGINE IN FAILURE AND FAULT
Monge-Concepción et al. Evaluating the effect of vane trailing edge flow on turbine rim sealing
RU2656083C1 (en) Method of operation of gas turbine engine
US20230315950A1 (en) Clearance calculation device and clearance calculation method

Legal Events

Date Code Title Description
QB4A Licence on use of patent

Effective date: 20101007

QZ41 Official registration of changes to a registered agreement (patent)

Free format text: LICENCE FORMERLY AGREED ON 20101007

Effective date: 20110826

PD4A Correction of name of patent owner