F05D 2260/36
By a form fit connection
Official title: by a form fit connection, e.g. by interlocking
F05D2260/36 (By a form fit connection) appears on 730 US grants and 838 published applications in this corpus.
Search patents in F05D- Granted patents
- 730
- Published applications
- 838
- Assignees
- 217
- Inventors
- 1,759
- Latest grant
- 18 Aug 2026
Filings by year
| Year | Granted patents | Published applications |
|---|---|---|
| 1977 | 1 | 0 |
| 1978 | 1 | 0 |
| 1979 | 0 | 0 |
| 1980 | 0 | 0 |
| 1981 | 1 | 0 |
| 1982 | 0 | 0 |
| 1983 | 1 | 0 |
| 1984 | 0 | 0 |
| 1985 | 0 | 0 |
| 1986 | 0 | 0 |
| 1987 | 0 | 0 |
| 1988 | 1 | 0 |
| 1989 | 0 | 0 |
| 1990 | 0 | 0 |
| 1991 | 0 | 0 |
| 1992 | 0 | 0 |
| 1993 | 0 | 0 |
| 1994 | 0 | 0 |
| 1995 | 0 | 0 |
| 1996 | 2 | 0 |
| 1997 | 1 | 0 |
| 1998 | 2 | 0 |
| 1999 | 1 | 0 |
| 2000 | 2 | 0 |
| 2001 | 0 | 0 |
| 2002 | 1 | 0 |
| 2003 | 1 | 0 |
| 2004 | 0 | 3 |
| 2005 | 0 | 1 |
| 2006 | 2 | 4 |
| 2007 | 3 | 5 |
| 2008 | 2 | 9 |
| 2009 | 1 | 5 |
| 2010 | 2 | 16 |
| 2011 | 10 | 21 |
| 2012 | 8 | 23 |
| 2013 | 8 | 17 |
| 2014 | 23 | 20 |
| 2015 | 21 | 36 |
| 2016 | 14 | 50 |
| 2017 | 23 | 54 |
| 2018 | 43 | 80 |
| 2019 | 75 | 71 |
| 2020 | 90 | 69 |
| 2021 | 71 | 79 |
| 2022 | 93 | 62 |
| 2023 | 69 | 70 |
| 2024 | 79 | 55 |
| 2025 | 52 | 39 |
| 2026 | 26 | 49 |
By publication year. Applications have been published since 2001. 2026 runs to 8 Oct.
Recent patents
- Turbine shroud assembly with carrier cooling holes for carrier aft flange18 Aug 2026US 12,709,993 B1ROLLS-ROYCE plc
- Propulsor fan and drive system23 Jun 2026US 12,662,943 B2Whisper Aero Inc.
- Locking system for a thrust reverser of an aircraft9 Jun 2026US 12,650,099 B1The Boeing Company
- Non rotating spacer for gas turbine engine9 Jun 2026US 12,650,185 B2Pratt & Whitney Rzeszow S.A.
- Modularity of an aircraft turbomachine26 May 2026US 12,637,982 B2Safran Aircraft Engines
- Guide Vane Segment17 Sep 2026US 2026/0275876 A1MTU Aero Engines AG
- Hydrostatic annular seal10 Sep 2026US 2026/0266188 A1Safran Aircraft Engines
- Stator assembly for an aircraft turbine engine10 Sep 2026US 2026/0266190 A1Safran Aircraft Engines
- Gas turbine engines with blade assemblies having cooling holes3 Sep 2026US 2026/0258731 A1General Electric Company
- Turbomachine assembly comprising platforms having edges provided with complementary protrusions and notches and associated turbomachine27 Aug 2026US 2026/0251070 A1Safran Aircraft Engines
Most cited
By later US patents
- High pressure gas generator rotor tie rod system for gas turbine engine130US 5,537,814 AGeneral Electric Company · 1996
- Reinforced compressor rotor coupling76US 5,628,621 AGeneral Electric Company · 1997
- Separable blade platform50US 7,284,958 B2Allison Advanced Development Company · 2007
- Composite air cooled turbine rotor blade48US 8,366,392 B1Florida Turbine Technologies, Inc. · 2013
- Impact absorbing blade mounts for variable pitch blades46US 4,047,840 AThe United States of America as represented by the Administrator of the National Aeronautics and Space Administration · 1977