Small diameter gas turbine engine
US5207054A · kind A · utility
29Cited by
16References
23Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Apr 24, 1991 |
| Grant date | May 4, 1993 |
| Priority date | — |
| Expiry date | Apr 24, 2011 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02C7/27
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The diameter of a gas turbine engine may be reduced through the use of a construction including a monorotor (44) journaled for rotation and mounting compressor blades (48) at one end (46) and turbine blades (56) at an opposite end (54). An axial diffuser (96) receives the discharge from the compressor blades (84) and is contained in a plenum (98). A reverse flow, annular combustor (83) is disposed about the rotor (44) and has a dome (100) whose height is a minor fraction of the axial length of the combustor (83) and which discharges to an annular turbine nozzle (77) having axial turbine nozzle blades (76).
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.