SU469311A1 - COOLING SYSTEM OF EQUIPMENT ON AIRCRAFT - Google Patents

COOLING SYSTEM OF EQUIPMENT ON AIRCRAFT

Info

Publication number
SU469311A1
SU469311A1 SU1807190/23A SU1807190A SU469311A1 SU 469311 A1 SU469311 A1 SU 469311A1 SU 1807190/23 A SU1807190/23 A SU 1807190/23A SU 1807190 A SU1807190 A SU 1807190A SU 469311 A1 SU469311 A1 SU 469311A1
Authority
SU
USSR - Soviet Union
Prior art keywords
equipment
heat exchanger
pump
cooling system
flow regulator
Prior art date
Application number
SU1807190/23A
Other languages
Russian (ru)
Inventor
Н.С. Николаев
И.Д. Кузнецов
В.П. Муравьев
А.А. Абрамян
Е.А. Заркевич
Н.И. Рудченко
Original Assignee
Н.С. Николаев
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 Н.С. Николаев filed Critical Н.С. Николаев
Priority to SU1807190/23A priority Critical patent/SU469311A1/en
Application granted granted Critical
Publication of SU469311A1 publication Critical patent/SU469311A1/en

Links

Abstract

Система охлаждения оборудования на летательном аппарате, содержащая теплообменник, установленный по тракту теплоносителя в замкнутом контуре между насосом и охлаждаемым оборудованием, а по тракту холодоносителя на магистрали, соединяющей теплообменник с компрессором двигателя через первичный продувочный радиатор и снабженный промежуточным воздушно-испарительным радиатором турбохолодильник, а также регулятор расхода холодного воздуха и заслонку на линии пропуска горячего воздуха, блок управления которой подключен к датчику температуры теплоносителя, отличающаяся тем, что, с целью улучшения параметров термостатирования оборудования, регулятор расхода холодного воздуха установлен между первичным радиатором и компрессором турбохолодильника и подключен к датчику температуры, установленному в контуре между насосом и теплообменником.Equipment cooling system on an aircraft containing a heat exchanger installed along the coolant path in a closed circuit between the pump and the equipment to be cooled, and along the coolant path on the main line connecting the heat exchanger to the engine compressor via the primary purge radiator and equipped with an intermediate air-evaporating radiator a turbo-cooler, and cold air flow regulator and damper on the hot air inlet line, the control unit of which is connected to the temp sensor Aturi coolant, characterized in that, in order to improve the thermostating equipment parameters, the cold air flow regulator installed between the primary cooler and the compressor cooling turbines and connected to a temperature sensor installed in the circuit between the pump and the heat exchanger.

SU1807190/23A 1972-07-10 1972-07-10 COOLING SYSTEM OF EQUIPMENT ON AIRCRAFT SU469311A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
SU1807190/23A SU469311A1 (en) 1972-07-10 1972-07-10 COOLING SYSTEM OF EQUIPMENT ON AIRCRAFT

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SU1807190/23A SU469311A1 (en) 1972-07-10 1972-07-10 COOLING SYSTEM OF EQUIPMENT ON AIRCRAFT

Publications (1)

Publication Number Publication Date
SU469311A1 true SU469311A1 (en) 2005-12-27

Family

ID=60520550

Family Applications (1)

Application Number Title Priority Date Filing Date
SU1807190/23A SU469311A1 (en) 1972-07-10 1972-07-10 COOLING SYSTEM OF EQUIPMENT ON AIRCRAFT

Country Status (1)

Country Link
SU (1) SU469311A1 (en)

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