F02K 3/02
In which part of the working fluid by-passes the turbine and combustion
Official title: in which part of the working fluid by-passes the turbine and combustion chamber
F02K3/02 (In which part of the working fluid by-passes the turbine and combustion) appears on 3,619 US grants and 4,304 published applications in this corpus.
Search patents in F02K- Granted patents
- 3,619
- Published applications
- 4,304
- Assignees
- 260
- Inventors
- 3,943
- Latest grant
- 6 Oct 2026
Filings by year
| Year | Granted patents | Published applications |
|---|---|---|
| 1976 | 9 | 0 |
| 1977 | 15 | 0 |
| 1978 | 7 | 0 |
| 1979 | 4 | 0 |
| 1980 | 10 | 0 |
| 1981 | 9 | 0 |
| 1982 | 1 | 0 |
| 1983 | 4 | 0 |
| 1984 | 7 | 0 |
| 1985 | 4 | 0 |
| 1986 | 5 | 0 |
| 1987 | 4 | 0 |
| 1988 | 13 | 0 |
| 1989 | 10 | 0 |
| 1990 | 14 | 0 |
| 1991 | 11 | 0 |
| 1992 | 13 | 0 |
| 1993 | 18 | 0 |
| 1994 | 15 | 0 |
| 1995 | 14 | 0 |
| 1996 | 2 | 0 |
| 1997 | 6 | 0 |
| 1998 | 14 | 0 |
| 1999 | 6 | 0 |
| 2000 | 7 | 0 |
| 2001 | 8 | 1 |
| 2002 | 13 | 13 |
| 2003 | 18 | 28 |
| 2004 | 22 | 30 |
| 2005 | 25 | 35 |
| 2006 | 17 | 54 |
| 2007 | 26 | 65 |
| 2008 | 29 | 127 |
| 2009 | 48 | 127 |
| 2010 | 72 | 136 |
| 2011 | 92 | 103 |
| 2012 | 94 | 109 |
| 2013 | 106 | 192 |
| 2014 | 127 | 168 |
| 2015 | 146 | 186 |
| 2016 | 91 | 298 |
| 2017 | 119 | 333 |
| 2018 | 238 | 346 |
| 2019 | 332 | 281 |
| 2020 | 366 | 409 |
| 2021 | 312 | 233 |
| 2022 | 280 | 183 |
| 2023 | 235 | 223 |
| 2024 | 247 | 185 |
| 2025 | 208 | 226 |
| 2026 | 126 | 213 |
By publication year. Applications have been published since 2001. 2026 runs to 8 Oct.
Subgroups
Granted patents
Recent patents
- Aircraft with an unducted fan propulsor6 Oct 2026US 12,752,923 B2General Electric Company
- Inducer assembly for a turbine engine29 Sep 2026US 12,746,491 B2General Electric Company
- Flexible support structure for a geared architecture gas turbine engine29 Sep 2026US 12,747,675 B2Rtx Corporation
- Gas turbine engine with acoustic spacing of the fan blades and outlet guide vanes29 Sep 2026US 12,747,699 B2General Electric Company
- Gas turbine engine with acoustic spacing of the fan blades and outlet guide vanes29 Sep 2026US 12,747,700 B2General Electric Company
- Radius ratio high-speed shaft rating for turbine engines8 Oct 2026US 2026/0309105 A1General Electric Company
- Actuatable airflow splitter for aircraft propulsion system1 Oct 2026US 2026/0296664 A1Rtx Corporation
- Compact gear train for turbomachine reducer1 Oct 2026US 2026/0298150 A1Safran Transmission Systems
- Superconducting ultra power efficient radial fan augmented nano-aerodrive (superfan)1 Oct 2026US 2026/0298178 A1Sonic Blue Aerospace, Inc.
- Flow deflector having channels with double ejection angles1 Oct 2026US 2026/0298265 A1Safran Aircraft Engines
Most cited
By later US patents
- Variable area fan exhaust nozzle having mechanically separate sleeve and thrust reverser actuation systems474US 5,778,659 AUnited Technologies Corporation · 1998
- Low solidity turbofan352US 7,374,403 B2General Electric Company · 2008
- Aircraft engine with inter-turbine engine frame supported counter rotating low pressure turbine rotors329US 6,619,030 B1General Electric Company · 2003
- Counter rotating aircraft gas turbine engine with high overall pressure ratio compressor248US 6,732,502 B2General Electric Company · 2004
- Turbofan gas turbine engine242US 4,827,712 AROLLS-ROYCE plc · 1989