Additive injection system for improving thermal stability of jet fuel
US8234870B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Apr 17, 2009 |
| Grant date | Aug 7, 2012 |
| Priority date | — |
| Expiry date | Apr 17, 2031 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T137/2499
- WIPO fieldControl
- WIPO sectorInstruments
Abstract
A gas turbine engine fuel system includes a fuel tank for storing fuel, a heat exchanger through which the fuel from the fuel tank can pass, a fuel pump located downstream from the heat exchanger for pumping the fuel, a fuel metering unit for metering the fuel pumped by the fuel pump, an additive tank for storing a fuel additive, an additive delivery subsystem for mixing the fuel additive with the fuel at or before the heat exchanger to generate a fuel and fuel additive mixture, and a combustor located downstream of the fuel metering unit where the fuel and fuel additive mixture is delivered for combustion. The fuel additive comprises a fuel stabilizer for reducing fuel coking.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.