SU275762A1 - Device for low-temperature testing of aircraft instruments in the flow of cooling gas - Google Patents

Device for low-temperature testing of aircraft instruments in the flow of cooling gas

Info

Publication number
SU275762A1
SU275762A1 SU1278011/23A SU1278011A SU275762A1 SU 275762 A1 SU275762 A1 SU 275762A1 SU 1278011/23 A SU1278011/23 A SU 1278011/23A SU 1278011 A SU1278011 A SU 1278011A SU 275762 A1 SU275762 A1 SU 275762A1
Authority
SU
USSR - Soviet Union
Prior art keywords
low
tube
cooling gas
temperature testing
flow
Prior art date
Application number
SU1278011/23A
Other languages
Russian (ru)
Inventor
Г.И. Воронин
В.Н. Сивец
Д.П. Балакирев
Б.А. Кононов
Ю.В. Антонов
Ю.В. Чижиков
В.К. Евстратов
Original Assignee
Г.И. Воронин
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 Г.И. Воронин filed Critical Г.И. Воронин
Priority to SU1278011/23A priority Critical patent/SU275762A1/en
Application granted granted Critical
Publication of SU275762A1 publication Critical patent/SU275762A1/en

Links

Abstract

Устройство для низкотемпературных испытаний авиационных приборов в потоке охлаждающего газа, содержащее заключенную внутри корпуса вихревую трубку, соединенную с источником сжатого газа, и двухстенную камеру для размещения испытываемых приборов, отличающееся тем, что, с целью обеспечения возможности проведения испытаний непосредственно на объекте, вихревая трубка установлена внутри ограниченного корпусом кольцевого проточного канала, сообщающего обращенный в камеру холодный конец трубки с атмосферой через отсасывающий эжектор, образованный горячим концом трубки и корпусом, снабженным эластичным кожухом, прижимаемым к охватываемой им наружной стенке камеры, установленной на объекте, благодаря разрежению в кольцевом канале и камере, создаваемому при работу вихревой трубки.A device for low-temperature testing of aircraft instruments in a cooling gas flow, containing a vortex tube inside the case connected to a source of compressed gas, and a double-walled chamber for accommodating the tested instruments, characterized in that, in order to enable testing directly at the facility, the vortex tube is installed inside the annular flow channel bounded by the casing, which informs the cold end of the tube with the atmosphere through the suction ejector, about developed by the hot end of the tube and the case, equipped with an elastic casing, pressed against the outer wall of the chamber, which is mounted on the object, due to the vacuum in the annular channel and the chamber created during the operation of the vortex tube.

SU1278011/23A 1968-10-21 1968-10-21 Device for low-temperature testing of aircraft instruments in the flow of cooling gas SU275762A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
SU1278011/23A SU275762A1 (en) 1968-10-21 1968-10-21 Device for low-temperature testing of aircraft instruments in the flow of cooling gas

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SU1278011/23A SU275762A1 (en) 1968-10-21 1968-10-21 Device for low-temperature testing of aircraft instruments in the flow of cooling gas

Publications (1)

Publication Number Publication Date
SU275762A1 true SU275762A1 (en) 2006-02-27

Family

ID=60514342

Family Applications (1)

Application Number Title Priority Date Filing Date
SU1278011/23A SU275762A1 (en) 1968-10-21 1968-10-21 Device for low-temperature testing of aircraft instruments in the flow of cooling gas

Country Status (1)

Country Link
SU (1) SU275762A1 (en)

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