Gas turbine engine axial compressor rear hub
Number of patents in Portfolio can not be more than 2000
United States of America Patent
Stats
-
Jan 30, 2018
Issued Date -
N/A
app pub date -
Jul 7, 2015
filing date -
Jul 31, 2014
priority date (Note) -
In Force
status (Latency Note)
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Abstract
A gas turbine engine includes an axial high pressure compressor includes a rear hub disposed aft of an aft rotor segment. The rear hub includes an inner surface, an outer surface, and a sealing face, wherein the sealing face is sealingly engaged with the aft rotor segment, and in fluid communication with the cooling channel. The cooling channels are configured to delivery air to contact the inner surface of the rear hub.
First Claim
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International Classification(s)
- 2015 Application Filing Year
- F04D Class
- 1667 Applications Filed
- 1242 Patents Issued To-Date
- 74.51 % Issued To-Date
Cited Art Landscape
Patent Citation Ranking
- 0 Citation Count
- F04D Class
- 0 % this patent is cited more than
- 7 Age
Maintenance Fees
| Fee | Large entity fee | small entity fee | micro entity fee | due date |
|---|---|---|---|---|
| 7.5 Year Payment | $3600.00 | $1800.00 | $900.00 | Jul 30, 2025 |
| 11.5 Year Payment | $7400.00 | $3700.00 | $1850.00 | Jul 30, 2029 |
