SU396959A1 - Device for controlling the humidity of the air on an aircraft - Google Patents

Device for controlling the humidity of the air on an aircraft

Info

Publication number
SU396959A1
SU396959A1 SU1735773/23A SU1735773A SU396959A1 SU 396959 A1 SU396959 A1 SU 396959A1 SU 1735773/23 A SU1735773/23 A SU 1735773/23A SU 1735773 A SU1735773 A SU 1735773A SU 396959 A1 SU396959 A1 SU 396959A1
Authority
SU
USSR - Soviet Union
Prior art keywords
turbine
air
supply line
cooler
aircraft
Prior art date
Application number
SU1735773/23A
Other languages
Russian (ru)
Inventor
Р.З. Гальперин
В.И. Слотин
Original Assignee
Р.З. Гальперин
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 Р.З. Гальперин filed Critical Р.З. Гальперин
Priority to SU1735773/23A priority Critical patent/SU396959A1/en
Application granted granted Critical
Publication of SU396959A1 publication Critical patent/SU396959A1/en

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  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Система кондиционирования воздуха на сверхзвуковом самолете, содержащая последовательно установленные на магистрали подачи воздуха продувочный и испарительный радиаторы и турбину турбохолодильника, а также обводную линию горячего воздуха, подключенную к магистрали подачи между турбиной и гермокабиной, оборудованной регулятором температуры, управляющим заслонкой на обводной линии, отличающаяся тем, что, с целью повышения эффективности системы при использовании турбохолодильника с сопловым аппаратом, регулируемым при помощи мерного устройства, установленного за турбиной, обводная линия подключена к магистрали подачи воздуха перед мерным устройством регулятора соплового аппарата турбины.Air conditioning system on a supersonic aircraft containing purge and evaporative radiators and a turbine cooler turbine installed sequentially on the air supply line, as well as a hot air bypass line connected to the supply line between the turbine and pressurized cabin equipped with a temperature controller operating a bypass valve, characterized by that, with the aim of increasing the efficiency of the system when using a turbo-cooler with a nozzle apparatus, adjustable by means of About the device installed behind the turbine, the bypass line is connected to the air supply line in front of the measuring device of the regulator of the turbine nozzle.

SU1735773/23A 1972-01-10 1972-01-10 Device for controlling the humidity of the air on an aircraft SU396959A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
SU1735773/23A SU396959A1 (en) 1972-01-10 1972-01-10 Device for controlling the humidity of the air on an aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SU1735773/23A SU396959A1 (en) 1972-01-10 1972-01-10 Device for controlling the humidity of the air on an aircraft

Publications (1)

Publication Number Publication Date
SU396959A1 true SU396959A1 (en) 2006-02-10

Family

ID=60514809

Family Applications (1)

Application Number Title Priority Date Filing Date
SU1735773/23A SU396959A1 (en) 1972-01-10 1972-01-10 Device for controlling the humidity of the air on an aircraft

Country Status (1)

Country Link
SU (1) SU396959A1 (en)

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