RU2014111002A

RU2014111002A - FUEL AIRCRAFT SYSTEM

Info

Publication number: RU2014111002A
Application number: RU2014111002/11A
Authority: RU
Inventors: Николай Григорьевич Кликодуев; Анатолий Петрович Мищенко
Original assignee: Российская Федерация, от имени которой выступает Министерство обороны Российской Федерации
Priority date: 2014-03-21
Filing date: 2014-03-21
Publication date: 2015-09-27
Also published as: RU2565428C1

Abstract

1. Топливная система летательного аппарата, содержащая многоотсечный топливный бак, полости отсеков которого сообщены последовательно магистралями перелива топлива с последним отсеком и через него с двигателем летательного аппарата, а через первый отсек линией наддува с системой подачи газа избыточного давления, содержащей пусковое устройство и устройство ограничения расхода газа, отличающаяся тем, что магистраль перелива топлива в полость, по крайней мере, последнего отсека топливного бака снабжена обратным клапаном, при этом полость, по крайней мере, последнего отсека сообщена дополнительной линией наддува с системой подачи газа через дополнительное пусковое устройство и дополнительное устройство ограничения расхода газа, настроенное на увеличенное значение величины ограничения расхода газа.2. Топливная система по п.1, отличающаяся тем, что, по крайней мере, последний отсек топливного бака размещен в полости предыдущего отсека с обеспечением зазоров между стенками отсеков.1. The fuel system of the aircraft, containing a multi-compartment fuel tank, the cavity of the compartments of which are connected sequentially by the overflow lines with the last compartment and through it to the aircraft engine, and through the first compartment by a boost line with an overpressure gas supply system containing a starting device and a limiting device gas flow rate, characterized in that the fuel overflow line into the cavity of at least the last compartment of the fuel tank is equipped with a check valve, wherein the cavity at least the last compartment is communicated by an additional boost line to the gas supply system through an additional starting device and an additional gas flow restriction device configured to increase the value of the gas flow restriction. 2. The fuel system according to claim 1, characterized in that at least the last compartment of the fuel tank is placed in the cavity of the previous compartment with the provision of gaps between the walls of the compartments.

Claims

1. The fuel system of the aircraft, containing a multi-compartment fuel tank, the cavity of the compartments of which are connected sequentially by the overflow lines with the last compartment and through it to the aircraft engine, and through the first compartment by a boost line with an overpressure gas supply system containing a starting device and a limiting device gas flow rate, characterized in that the fuel overflow line into the cavity of at least the last compartment of the fuel tank is equipped with a check valve, wherein the cavity l, at least the last compartment is communicated by an additional line of pressurization with the gas supply system through an additional starting device and an additional gas flow limiting device, configured for an increased value of the gas flow limiting value.

2. The fuel system according to claim 1, characterized in that at least the last compartment of the fuel tank is placed in the cavity of the previous compartment with the provision of gaps between the walls of the compartments.