Compression section for an axial flow rotary machine
US4371311A · kind A · utility
20Cited by
8References
7Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Apr 28, 1980 |
| Grant date | Feb 1, 1983 |
| Priority date | — |
| Expiry date | Apr 28, 2000 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A compression section of a gas turbine engine having an annular flow path is disclosed. Various construction details which increase the efficiency of an array of rotor blades in the compression section are developed. The annular flow path is contoured to cause the streamlines of the flow path to follow a pattern of varying radial curvature. In one embodiment, a conical surface extending between the base of each airfoil on the inner wall causes a flow path contraction and a cylindrical surface on the outer wall facing the tip of each airfoil enables close clearances.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.