F02C 3/06
The compressor comprising only axial stages
Official title: the compressor comprising only axial stages (F02C3/10 takes precedence)
F02C3/06 (The compressor comprising only axial stages) appears on 676 US grants and 761 published applications in this corpus.
Search patents in F02C- Granted patents
- 676
- Published applications
- 761
- Assignees
- 109
- Inventors
- 1,034
- Latest grant
- 29 Sep 2026
Filings by year
| Year | Granted patents | Published applications |
|---|---|---|
| 1976 | 4 | 0 |
| 1977 | 0 | 0 |
| 1978 | 1 | 0 |
| 1979 | 0 | 0 |
| 1980 | 1 | 0 |
| 1981 | 1 | 0 |
| 1982 | 0 | 0 |
| 1983 | 0 | 0 |
| 1984 | 1 | 0 |
| 1985 | 1 | 0 |
| 1986 | 1 | 0 |
| 1987 | 0 | 0 |
| 1988 | 4 | 0 |
| 1989 | 7 | 0 |
| 1990 | 4 | 0 |
| 1991 | 3 | 0 |
| 1992 | 6 | 0 |
| 1993 | 2 | 0 |
| 1994 | 4 | 0 |
| 1995 | 3 | 0 |
| 1996 | 0 | 0 |
| 1997 | 0 | 0 |
| 1998 | 1 | 0 |
| 1999 | 2 | 0 |
| 2000 | 3 | 0 |
| 2001 | 4 | 0 |
| 2002 | 7 | 1 |
| 2003 | 4 | 6 |
| 2004 | 10 | 6 |
| 2005 | 1 | 6 |
| 2006 | 3 | 20 |
| 2007 | 9 | 13 |
| 2008 | 7 | 26 |
| 2009 | 12 | 32 |
| 2010 | 9 | 11 |
| 2011 | 29 | 11 |
| 2012 | 14 | 11 |
| 2013 | 9 | 28 |
| 2014 | 15 | 18 |
| 2015 | 18 | 36 |
| 2016 | 14 | 49 |
| 2017 | 20 | 31 |
| 2018 | 38 | 49 |
| 2019 | 34 | 72 |
| 2020 | 82 | 78 |
| 2021 | 59 | 48 |
| 2022 | 50 | 26 |
| 2023 | 43 | 43 |
| 2024 | 52 | 51 |
| 2025 | 55 | 50 |
| 2026 | 29 | 39 |
By publication year. Applications have been published since 2001. 2026 runs to 8 Oct.
Subgroups
Granted patents
Recent patents
- Fluid injection system and method for mitigating rotating stall in turbine engine29 Sep 2026US 12,747,705 B2GE Vernova Infrastructure Technology LLC
- Turbine engine having a compression section22 Sep 2026US 12,742,419 B1General Electric Company
- Additively manufactured gas turbine engine and ventilator15 Sep 2026US 12,735,995 B2Technion Research & Development Foundation Limited
- Gas turbine engine8 Sep 2026US 12,729,649 B2General Electric Company
- Triple-flow axial turbomachine comprising a diverging heat exchanger in the third flow1 Sep 2026US 12,723,545 B2Safran Aero Boosters SA
- Gas turbine engine with improved heat management8 Oct 2026US 2026/0309080 A1ROLLS-ROYCE plc
- Turbofan engine including a fan actuation system8 Oct 2026US 2026/0309162 A1General Electric Company
- Turbofan engine converted from producing thrust power to producing shaft power and corresponding method1 Oct 2026US 2026/0298135 A1TJet Holdings Inc.
- Superconducting ultra power efficient radial fan augmented nano-aerodrive (superfan)1 Oct 2026US 2026/0298178 A1Sonic Blue Aerospace, Inc.
- Turbofan engine including a fan actuation system24 Sep 2026US 2026/0286973 A1General Electric Company
Most cited
By later US patents
- Aircraft engine with inter-turbine engine frame supported counter rotating low pressure turbine rotors329US 6,619,030 B1General Electric Company · 2003
- Geared counterrotating turbine/fan propulsion system226US 5,010,729 AGeneral Electric Company · 1991
- Gas turbine engine rotor support system219US 5,361,580 AGeneral Electric Company · 1994
- Nested core gas turbine engine195US 7,219,490 B2D-Star Engineering · 2007
- High bypass ratio counterrotating turbofan engine172US 4,790,133 AGeneral Electric Company · 1988