High compression gas turbine with superheat enhancement
US7600368B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Jul 3, 2007 |
| Grant date | Oct 13, 2009 |
| Priority date | — |
| Expiry date | May 22, 2028 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02C3/10
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A system and method for adding superheat to the hot process gas at the discharge of a compressor drive turbine of a high compression ratio gas turbine or aviation gas turbine. The superheat brings the temperature ratio (T2/T1) of the power output turbine into equality with the pressure ratio (P2/P1)(K−1)/K to effect a highly efficient and adiabatic isentropic expansion across the power output turbine. The added superheat contributes to the output power of the engine less any inefficiency of the output power turbine. All of the variables are brought together to develop the proper superheat levels for obtaining the greatest power output possible at minimum fuel consumption levels.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.