High compression gas turbine with superheat enhancement
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United States of America Patent
Stats
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Aug 14, 2007
Grant Date -
Jul 12, 2007
app pub date -
Jan 6, 2004
filing date -
Jan 7, 2003
priority date (Note) -
In Force
status (Latency Note)
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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).sup.(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.
First Claim
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Family
| Country | kind | publication No. | Filing Date |
|---|---|---|---|
| WO | A2 | WO2005003533 | Jan 07, 2004 |
| US | B2 | US7600368 | Jul 03, 2007 |
International Classification(s)
- 2004 Application Filing Year
- F02C Class
- 446 Applications Filed
- 282 Patents Issued To-Date
- 63.23 % Issued To-Date
Cited Art Landscape
Patent Citation Ranking
- 20 Citation Count
- F02C Class
- 52.88 % this patent is cited more than
- 18 Age
