Multiple passage cooling circuit method and device for gas turbine engine fuel nozzle
US5570580A · kind A · utility
85Cited by
10References
20Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Jul 18, 1994 |
| Grant date | Nov 5, 1996 |
| Priority date | — |
| Expiry date | Jul 18, 2014 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05B2220/302
- WIPO fieldThermal processes and apparatus
- WIPO sectorMechanical engineering
Abstract
A gas turbine fuel nozzle and method of fuel flow provide resistance to coking of the fuel by means of a multiple passage heat transfer cooling circuit. Fuel streams to primary and secondary sprays of pilot and main nozzle tips are arranged to transfer heat between the pilot primary fuel stream and each of the main secondary fuel stream and the pilot secondary fuel stream. This protects the fuel in the streams from coking during both low flow, lower engine heat conditions and high flow, high engine heat conditions. This nozzle and flow can protect engines with both single tip and dual tip nozzles.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.