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 gasInfo
- 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
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.
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) |
-
1968
- 1968-10-21 SU SU1278011/23A patent/SU275762A1/en active
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