F02K 1/30
For varying effective area of jet pipe or nozzle
Official title: for varying effective area of jet pipe or nozzle
F02K1/30 (For varying effective area of jet pipe or nozzle) appears on 92 US grants and 94 published applications in this corpus.
Search patents in F02K- Granted patents
- 92
- Published applications
- 94
- Assignees
- 37
- Inventors
- 157
- Latest grant
- 24 Feb 2026
Filings by year
| Year | Granted patents | Published applications |
|---|---|---|
| 1990 | 1 | 0 |
| 1991 | 0 | 0 |
| 1992 | 0 | 0 |
| 1993 | 0 | 0 |
| 1994 | 1 | 0 |
| 1995 | 0 | 0 |
| 1996 | 0 | 0 |
| 1997 | 2 | 0 |
| 1998 | 2 | 0 |
| 1999 | 1 | 0 |
| 2000 | 3 | 0 |
| 2001 | 0 | 0 |
| 2002 | 1 | 0 |
| 2003 | 1 | 1 |
| 2004 | 0 | 0 |
| 2005 | 1 | 2 |
| 2006 | 1 | 3 |
| 2007 | 1 | 3 |
| 2008 | 0 | 4 |
| 2009 | 3 | 8 |
| 2010 | 2 | 6 |
| 2011 | 5 | 3 |
| 2012 | 4 | 6 |
| 2013 | 8 | 10 |
| 2014 | 4 | 4 |
| 2015 | 2 | 9 |
| 2016 | 3 | 10 |
| 2017 | 12 | 5 |
| 2018 | 10 | 8 |
| 2019 | 8 | 6 |
| 2020 | 2 | 1 |
| 2021 | 6 | 3 |
| 2022 | 5 | 0 |
| 2023 | 2 | 1 |
| 2024 | 0 | 0 |
| 2025 | 0 | 1 |
| 2026 | 1 | 0 |
By publication year. Applications have been published since 2001. 2026 runs to 8 Oct.
Recent patents
- Gas turbine engine with third stream24 Feb 2026US 12,560,132 B2General Electric Company
- Variable area nozzle assembly26 Sep 2023US 11,767,806 B1Rohr, Inc.
- System for controlling speed transition and thrust vectorisation in a multiple-shaped nozzle by secondary injection30 May 2023US 11,661,910 B2Centre National De La Recherche Scientifique
- Gas turbine engine with axial movable fan variable area nozzle27 Sep 2022US 11,454,193 B2Raytheon Technologies Corporation
- Split sleeve hidden door thrust reverser6 Sep 2022US 11,434,850 B2Rohr, Inc.
- Gas turbine engine with third stream10 Apr 2025US 2025/0116243 A1General Electric Company
- Variable area nozzle assembly7 Sep 2023US 2023/0279826 A1Rohr, Inc.
- Gas turbine engine with axial movable fan variable area nozzle16 Sep 2021US 2021/0285397 A1Raytheon Technologies Corporation
- Gas turbine engine bifurcation located fan variable area nozzle15 Jul 2021US 2021/0215120 A1Raytheon Technologies Corporation
- System for controlling speed transition and thrust vectorisation in a multiple-shaped nozzle by secondary injection3 Jun 2021US 2021/0164418 A1Centre National De La Recherche Scientifique
Most cited
By later US patents
- Turbofan engine with a core driven supercharged bypass duct and fixed geometry nozzle111US 5,806,303 AGeneral Electric Company · 1998
- Gas turbine engine with axial movable fan variable area nozzle62US 8,074,440 B2United Technologies Corporation · 2011
- Method and apparatus of asymmetric injection at the subsonic portion of a nozzle flow43US 6,112,513 ALockheed Martin Corporation · 2000
- Fluidic throat exhaust nozzle38US 5,996,936 AGeneral Electric Company · 1999
- Fluidic nozzle control system29US 6,336,319 B12002