Structure of output section of jet propulsion engine or gas turbine
US6099249A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Jun 17, 1997 |
| Grant date | Aug 8, 2000 |
| Priority date | — |
| Expiry date | Jun 17, 2017 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10S415/914
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A tandem blade lattice having characteristics enhanced is provided. In a high pressure ratio blade lattice, inevitable generation of an shock wave is shifted, as much as possible, toward a rear portion of an upper surface of a front blade to inhibit separation from a blade surface from being caused by interference of the shock wave and a boundary layer, and boundary layer control is performed such that a speed, a momentum and the like of a jet flowing from a trailing edge of a lower surface of the front blade onto an upper surface of a rear blade are regulated to obtain a flow along the upper surface of the rear blade, so that separation of the boundary layer on the upper surface of the rear blade is restricted to a vicinity of a trailing edge.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.