RU2014136783A - FUEL AIRCRAFT SYSTEM - Google Patents
FUEL AIRCRAFT SYSTEM Download PDFInfo
- Publication number
- RU2014136783A RU2014136783A RU2014136783A RU2014136783A RU2014136783A RU 2014136783 A RU2014136783 A RU 2014136783A RU 2014136783 A RU2014136783 A RU 2014136783A RU 2014136783 A RU2014136783 A RU 2014136783A RU 2014136783 A RU2014136783 A RU 2014136783A
- Authority
- RU
- Russia
- Prior art keywords
- fuel
- fuel tank
- cavity
- pressure
- supply line
- Prior art date
Links
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- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
1. Топливная система летательного аппарата, содержащая топливный бак, заправочную и дренажную горловины, снабженные клапанами перекрытия и сообщенные с полостью топливного бака, причем дренажная горловина сообщена с ее верхней частью, линию подачи топлива в двигатель, сообщенную с нижней частью полости топливного бака и снабженную пусковым клапаном, и линию подачи газа наддува, сообщенную с верхней частью полости топливного бака и снабженную пусковым клапаном, отличающаяся тем, что содержит, по крайней мере, один сигнализатор предельного давления в полости топливного бака, снабженный устройством коррекции давления срабатывания по температуре топлива.2. Топливная система по п. 1, отличающаяся тем, что устройство коррекции давления срабатывания по температуре топлива выполнено в виде упругого биметаллического элемента, на котором расположен один из контактов сигнализатора предельного давления и который размещен в его корпусе, при этом корпус закреплен на топливном баке с частичным размещением в объеме его полости, занимаемом топливом.1. The fuel system of the aircraft, containing a fuel tank, a filling and drainage neck, equipped with shutoff valves and communicated with the cavity of the fuel tank, and the drainage neck is in communication with its upper part, the fuel supply line to the engine in communication with the lower part of the fuel tank cavity and provided a start valve, and a boost gas supply line communicated with the upper part of the fuel tank cavity and equipped with a start valve, characterized in that it contains at least one limit switch o pressure in the cavity of the fuel tank, equipped with a device for correcting the response pressure according to the fuel temperature. 2. The fuel system according to claim 1, characterized in that the device for correcting the response pressure according to the fuel temperature is made in the form of an elastic bimetallic element on which one of the contacts of the pressure limit switch is located and which is located in its body, while the body is mounted on a fuel tank with a partial placement in the volume of its cavity occupied by fuel.
Claims (2)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2014136783A RU2014136783A (en) | 2014-09-11 | 2014-09-11 | FUEL AIRCRAFT SYSTEM |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2014136783A RU2014136783A (en) | 2014-09-11 | 2014-09-11 | FUEL AIRCRAFT SYSTEM |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| RU2014136783A true RU2014136783A (en) | 2016-04-10 |
Family
ID=55647427
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| RU2014136783A RU2014136783A (en) | 2014-09-11 | 2014-09-11 | FUEL AIRCRAFT SYSTEM |
Country Status (1)
| Country | Link |
|---|---|
| RU (1) | RU2014136783A (en) |
-
2014
- 2014-09-11 RU RU2014136783A patent/RU2014136783A/en not_active Application Discontinuation
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| FA92 | Acknowledgement of application withdrawn (lack of supplementary materials submitted) |
Effective date: 20160621 |