Fuel injector for a turbine engine
US5119636A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Dec 21, 1989 |
| Grant date | Jun 9, 1992 |
| Priority date | — |
| Expiry date | Dec 21, 2009 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02C7/22
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Manifold head effects at low fuel flows in a fuel injected air breathing turbine are minimized by utilizing fuel injectors having fuel injecting tubes (66) with open ends (70) for fuel injection and provided with elongated capillary tubes (88) upstream thereof and connected to receive fuel from a fuel manifold (48) having an inlet (56) while uniform, relatively low velocity fuel exit flow from the ends (70) the injecting tubes (66) is achieved through the use of internal impingement surfaces (96, 102, 106, 110, 124). Pressure loss differences contributing to nonuniform fuel flow and resulting from some fuel injecting tubes (66) be more distant from the manifold inlet (56) are minimized by shortening the length of the capillary tubes (88) furthest from the manifold inlet (56).
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.