F02K 1/383
With retractable elements
Official title: {with retractable elements}
F02K1/383 (With retractable elements) appears on 53 US grants and 38 published applications in this corpus.
Search patents in F02K- Granted patents
- 53
- Published applications
- 38
- Assignees
- 28
- Inventors
- 82
- Latest grant
- 20 Aug 2024
Filings by year
| Year | Granted patents | Published applications |
|---|---|---|
| 1983 | 1 | 0 |
| 1984 | 0 | 0 |
| 1985 | 1 | 0 |
| 1986 | 1 | 0 |
| 1987 | 0 | 0 |
| 1988 | 1 | 0 |
| 1989 | 0 | 0 |
| 1990 | 3 | 0 |
| 1991 | 0 | 0 |
| 1992 | 2 | 0 |
| 1993 | 2 | 0 |
| 1994 | 1 | 0 |
| 1995 | 1 | 0 |
| 1996 | 0 | 0 |
| 1997 | 0 | 0 |
| 1998 | 3 | 0 |
| 1999 | 2 | 0 |
| 2000 | 0 | 0 |
| 2001 | 1 | 0 |
| 2002 | 1 | 1 |
| 2003 | 0 | 1 |
| 2004 | 2 | 2 |
| 2005 | 1 | 3 |
| 2006 | 2 | 1 |
| 2007 | 1 | 2 |
| 2008 | 0 | 3 |
| 2009 | 2 | 0 |
| 2010 | 3 | 2 |
| 2011 | 0 | 2 |
| 2012 | 1 | 5 |
| 2013 | 3 | 2 |
| 2014 | 1 | 2 |
| 2015 | 3 | 2 |
| 2016 | 2 | 2 |
| 2017 | 4 | 1 |
| 2018 | 2 | 1 |
| 2019 | 0 | 0 |
| 2020 | 0 | 2 |
| 2021 | 2 | 1 |
| 2022 | 0 | 1 |
| 2023 | 2 | 2 |
| 2024 | 2 | 0 |
By publication year. Applications have been published since 2001.
Recent patents
- Variable area nozzle assembly for an aircraft propulsion system20 Aug 2024US 12,065,937 B1Rtx Corporation
- Confluence structure of a primary stream and a secondary stream in a bypass turbine engine16 Jan 2024US 11,873,783 B2Safran Aircraft Engines
- Aircraft propulsion system exhaust nozzle with ejector passage(s)12 Sep 2023US 11,754,018 B2Rohr, Inc.
- Confluence structure of a primary stream and a secondary stream in a bypass turbine engine27 Jun 2023US 11,686,274 B2Safran Aircraft Engines
- Turbofan comprising a set of rotatable blades for blocking off the bypass flow duct31 Aug 2021US 11,105,297 B2Airbus Operations GmbH
- Confluence structure of a primary stream and a secondary stream in a bypass turbine engine24 Aug 2023US 2023/0265814 A1Safran Aircraft Engines
- Aircraft propulsion system exhaust nozzle with ejector passage(s)22 Jun 2023US 2023/0193852 A1Rohr, Inc.
- Confluence structure of a primary stream and a secondary stream in a bypass turbine engine11 Aug 2022US 2022/0252023 A1Safran Aircraft Engines
- Gas turbine engine operating point11 Mar 2021US 2021/0071672 A1ROLLS-ROYCE plc
- Turbofan comprising a set of rotatable blades for blocking off the bypass flow duct30 Jul 2020US 2020/0240359 A1Airbus Operations GmbH
Most cited
By later US patents
- Jet engine with noise suppressing mixing and exhaust sections63US 5,269,139 AThe Boeing Company · 1993
- Confluent variable exhaust nozzle56US 6,751,944 B2The NORDAM Group, Inc. · 2004
- Exhaust assembly for a high speed civil transport aircraft engine44US 5,154,052 AGeneral Electric Company · 1992
- Variable shape, fluid flow nozzle for sound suppression38US 4,422,524 ALockheed Corporation · 1983
- Gas turbine engine exhaust nozzle having a noise attenuation device driven by shape memory material actuators34US 6,813,877 B2ROLLS-ROYCE plc · 2004