SU699352A1 - Pyrometer for measuring the temperature of gas turbine blades - Google Patents

Pyrometer for measuring the temperature of gas turbine blades

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Publication number
SU699352A1
SU699352A1 SU782615435A SU2615435A SU699352A1 SU 699352 A1 SU699352 A1 SU 699352A1 SU 782615435 A SU782615435 A SU 782615435A SU 2615435 A SU2615435 A SU 2615435A SU 699352 A1 SU699352 A1 SU 699352A1
Authority
SU
USSR - Soviet Union
Prior art keywords
temperature
measuring
pyrometer
turbine blades
gas turbine
Prior art date
Application number
SU782615435A
Other languages
Russian (ru)
Inventor
Эдуард Владимирович Асланян
Геральд Борисович Парфенов
Original Assignee
Предприятие П/Я В-2504
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 Предприятие П/Я В-2504 filed Critical Предприятие П/Я В-2504
Priority to SU782615435A priority Critical patent/SU699352A1/en
Application granted granted Critical
Publication of SU699352A1 publication Critical patent/SU699352A1/en

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Description

Изобретение относитс  к измерител ной технике дл  бесконтактного измер ни  температуры вращающихс  лопаток турбины по тепловому излучению нагре тых лопаток. Известны датчики пирометров дл  г зотурбинных двигателей, содержащие линзовую оптическую систему, круговую диафрагму и фотоприемник, устана ливаемле .на авиационном двигателе, позвол ющие определ ть распределени температуры по лопаткам при ее враще ний t И . Ближайшим техническим решением к изобретению  вл етс  пирометр дл  измерени  температуры лопаток газовой турбины, состо щий из датчика, содержащего оптическую систему,фотоприемник с полевой диафрагмой, и сог сующего усилител  2 . Поскольку датчик устанавливаетс  на некотором рассто нии от измер емой лопатки, ив- пространстве между ними движутс  высокотемпературные пр дукты Сгорани , то датчик воспринимает дополнительное излучение от свет щихс  образований в продуктах сгорани , что приводит к по влению гюгрвиности в измерении. Следует отметить, что с существующей тендвнцией роста температуры и давлени  газа вли ние мешающего излучени  растет и возникает необходимость в разработке эффективных мер борьбы с ним. Цель изобретени  увеличение точности измерени  температуры лопаток Турбины. Это достигаетс  тем, что в датчике установлен дополнительный фотоприемник так, что его ось визировани  составл ет с осью визировани  основного фотоприемника острый угол, а выход соединен через усилитель формировател  с управл ющим входом аналогового ключа, соедин ющего выход согласующего усилител  основного фотоприемника с входом аналогового запоминающего устройства. На чертеже дана функциональна  схема измерени  температур лопаток турбины пирометра. Она содержит камеру 1 сгорани , основной фотоприемник (датчик) J, до полнительный фотоприемник 3, измер емую область 4 на лопатке,область 5 низких температур, согласующий усилитель 6, усилитель 7 формировател .) однополюсный ключ 8, аналогониЯ пмпоминаютйй элемент 9, запом чиаюшийThe invention relates to a measurement technique for contactless measurement of the temperature of rotating turbine blades by thermal radiation of heated blades. Pyrometer sensors for zoturbine engines containing a lens optical system, a circular diaphragm, and a photoreceiver are known to be mounted on an aircraft engine, allowing determination of the temperature distribution of the blades during its rotation. The closest technical solution to the invention is a pyrometer for measuring the temperature of gas turbine blades, consisting of a sensor containing an optical system, a photodiode with a field diaphragm, and a matching amplifier 2. Since the sensor is installed at some distance from the measuring blade, the high-temperature Combustion Products move in the space between them, the sensor perceives additional radiation from the luminous formations in the combustion products, which leads to the appearance of rupture in the measurement. It should be noted that with the existing tendency for a rise in temperature and gas pressure, the influence of interfering radiation increases and there is a need to develop effective measures to control it. The purpose of the invention is to increase the accuracy of measuring the temperature of the turbine blades. This is achieved by installing an additional photodetector in the sensor so that its axis of sight is an acute angle with the axis of the main photodetector, and the output is connected via an amplifier of the driver to the control input of the analog switch that connects the output of the matching amplifier of the main photodetector to the input of the analogue memory devices. The drawing is a functional scheme for measuring the temperature of the blades of the pyrometer turbine. It contains a combustion chamber 1, the main photodetector (sensor) J, an additional photodetector 3, the measured area 4 on the paddle, the low temperature region 5, the matching amplifier 6, the amplifier 7 formatively.) A single-pole key 8, an analogy of the memory element 9, which is

SU782615435A 1978-03-13 1978-03-13 Pyrometer for measuring the temperature of gas turbine blades SU699352A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
SU782615435A SU699352A1 (en) 1978-03-13 1978-03-13 Pyrometer for measuring the temperature of gas turbine blades

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SU782615435A SU699352A1 (en) 1978-03-13 1978-03-13 Pyrometer for measuring the temperature of gas turbine blades

Publications (1)

Publication Number Publication Date
SU699352A1 true SU699352A1 (en) 1979-11-25

Family

ID=20764509

Family Applications (1)

Application Number Title Priority Date Filing Date
SU782615435A SU699352A1 (en) 1978-03-13 1978-03-13 Pyrometer for measuring the temperature of gas turbine blades

Country Status (1)

Country Link
SU (1) SU699352A1 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4797006A (en) * 1986-06-05 1989-01-10 Smiths Industries Public Limited Company Pyrometer systems for gas-turbine engines
US6698920B1 (en) * 2000-05-08 2004-03-02 General Electric Company Temperature measuring system and optical switch used therein

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4797006A (en) * 1986-06-05 1989-01-10 Smiths Industries Public Limited Company Pyrometer systems for gas-turbine engines
US6698920B1 (en) * 2000-05-08 2004-03-02 General Electric Company Temperature measuring system and optical switch used therein

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