F02C 3/064
The compressor having concentric stages
Official title: {the compressor having concentric stages}
F02C3/064 (The compressor having concentric stages) appears on 34 US grants and 38 published applications in this corpus.
Search patents in F02C- Granted patents
- 34
- Published applications
- 38
- Assignees
- 16
- Inventors
- 56
- Latest grant
- 17 Jun 2025
Filings by year
| Year | Granted patents | Published applications |
|---|---|---|
| 1988 | 1 | 0 |
| 1989 | 0 | 0 |
| 1990 | 0 | 0 |
| 1991 | 0 | 0 |
| 1992 | 0 | 0 |
| 1993 | 0 | 0 |
| 1994 | 0 | 0 |
| 1995 | 1 | 0 |
| 1996 | 0 | 0 |
| 1997 | 0 | 0 |
| 1998 | 0 | 0 |
| 1999 | 0 | 0 |
| 2000 | 0 | 0 |
| 2001 | 0 | 0 |
| 2002 | 0 | 1 |
| 2003 | 1 | 0 |
| 2004 | 0 | 1 |
| 2005 | 0 | 0 |
| 2006 | 2 | 1 |
| 2007 | 1 | 2 |
| 2008 | 0 | 0 |
| 2009 | 0 | 3 |
| 2010 | 0 | 1 |
| 2011 | 0 | 6 |
| 2012 | 3 | 1 |
| 2013 | 0 | 0 |
| 2014 | 3 | 1 |
| 2015 | 0 | 2 |
| 2016 | 0 | 1 |
| 2017 | 1 | 4 |
| 2018 | 5 | 1 |
| 2019 | 3 | 2 |
| 2020 | 2 | 4 |
| 2021 | 3 | 1 |
| 2022 | 3 | 1 |
| 2023 | 1 | 2 |
| 2024 | 3 | 2 |
| 2025 | 1 | 1 |
By publication year. Applications have been published since 2001.
Recent patents
- Air recuperated engine with air reinjection17 Jun 2025US 12,331,679 B2Rtx Corporation
- Turbine engine core and bypass flows having a defined fan-turbine radial distance10 Dec 2024US 12,163,464 B2ROLLS-ROYCE plc
- Air recuperated engine with air reinjection3 Sep 2024US 12,078,102 B2Rtx Corporation
- Adjustable guide vane with convexly shaped, radially inner storage section for a gas turbine, in particular an aircraft gas turbine6 Feb 2024US 11,892,012 B2MTU Aero Engines AG
- Operability geared turbofan engine including compressor section variable guide vanes10 Oct 2023US 11,781,490 B2Rtx Corporation
- Turbine engine core and bypass flows30 Jan 2025US 2025/0035037 A1ROLLS-ROYCE plc
- Air recuperated engine with air reinjection5 Dec 2024US 2024/0401523 A1Rtx Corporation
- Air recuperated engine with air reinjection28 Mar 2024US 2024/0102417 A1Raytheon Technologies Corporation
- Adjustable guide vane with convexly shaped, radially inner storage section for a gas turbine, in particular an aircraft gas turbine27 Jul 2023US 2023/0235752 A1MTU Aero Engines AG
- Turbine engine core and bypass flows26 Jan 2023US 2023/0028367 A1ROLLS-ROYCE plc
Most cited
By later US patents
- Nested core gas turbine engine195US 7,219,490 B2D-Star Engineering · 2007
- Nested core gas turbine engine61US 6,647,707 B22003
- Gas turbines with multiple gas flow paths35US 8,104,265 B2United Technologies Corporation · 2012
- Acoustically shielded exhaust system for high thrust jet engines19US 5,402,963 AGeneral Electric Company · 1995
- Method and apparatus for assembling gas turbine engines17US 7,144,221 B2General Electric Company · 2006