F01D 11/006
Sealing the gap between rotor blades or blades and rotor
Official title: {Sealing the gap between rotor blades or blades and rotor}
F01D11/006 (Sealing the gap between rotor blades or blades and rotor) appears on 874 US grants and 827 published applications in this corpus.
Search patents in F01D- Granted patents
- 874
- Published applications
- 827
- Assignees
- 110
- Inventors
- 1,581
- Latest grant
- 22 Sep 2026
Filings by year
| Year | Granted patents | Published applications |
|---|---|---|
| 1976 | 1 | 0 |
| 1977 | 5 | 0 |
| 1978 | 1 | 0 |
| 1979 | 0 | 0 |
| 1980 | 2 | 0 |
| 1981 | 1 | 0 |
| 1982 | 1 | 0 |
| 1983 | 1 | 0 |
| 1984 | 8 | 0 |
| 1985 | 11 | 0 |
| 1986 | 2 | 0 |
| 1987 | 4 | 0 |
| 1988 | 7 | 0 |
| 1989 | 7 | 0 |
| 1990 | 3 | 0 |
| 1991 | 2 | 0 |
| 1992 | 4 | 0 |
| 1993 | 11 | 0 |
| 1994 | 8 | 0 |
| 1995 | 8 | 0 |
| 1996 | 8 | 0 |
| 1997 | 3 | 0 |
| 1998 | 11 | 0 |
| 1999 | 10 | 0 |
| 2000 | 3 | 0 |
| 2001 | 12 | 1 |
| 2002 | 10 | 4 |
| 2003 | 13 | 4 |
| 2004 | 6 | 7 |
| 2005 | 3 | 18 |
| 2006 | 12 | 12 |
| 2007 | 13 | 15 |
| 2008 | 5 | 19 |
| 2009 | 11 | 22 |
| 2010 | 10 | 36 |
| 2011 | 20 | 26 |
| 2012 | 32 | 51 |
| 2013 | 33 | 47 |
| 2014 | 36 | 45 |
| 2015 | 38 | 61 |
| 2016 | 29 | 104 |
| 2017 | 51 | 66 |
| 2018 | 77 | 45 |
| 2019 | 65 | 48 |
| 2020 | 75 | 57 |
| 2021 | 72 | 52 |
| 2022 | 47 | 16 |
| 2023 | 26 | 24 |
| 2024 | 22 | 19 |
| 2025 | 27 | 11 |
| 2026 | 7 | 17 |
By publication year. Applications have been published since 2001. 2026 runs to 8 Oct.
Subgroups
Granted patents
Recent patents
- Gas turbine engine rotor stage with sealing members22 Sep 2026US 12,742,392 B2Pratt & Whitney Canada Corp.
- Gas turbine engine rotor stage with seal members15 Sep 2026US 12,735,990 B2Pratt & Whitney Canada Corp.
- Platform for a fan assembly14 Jul 2026US 12,680,464 B2Safran Aircraft Engines
- Combustor-vane interface feather seal23 Jun 2026US 12,662,945 B2Rtx Corporation
- Center tie rotor seal26 May 2026US 12,637,953 B1Rtx Corporation
- Turbine shroud ring assembly with improved load pathway1 Oct 2026US 2026/0298110 A1
- Gas turbine engine rotor stage with rotor blade damper arrangement10 Sep 2026US 2026/0266185 A1Rtx Corporation
- Rotor assembly with independent platforms and method for assembling such a rotor20 Aug 2026US 2026/0243168 A1
- Turbine ring assembly with improved axial pins20 Aug 2026US 2026/0243174 A1Safran Aircraft Engines
- Composite spacer ring and production method thereof6 Aug 2026US 2026/0225332 A1Safran
Most cited
By later US patents
- Turbine blade plateform sealing and vibration damping apparatus84US 4,872,812 AGeneral Electric Company · 1989
- Thermal control damper for turbine rotors82US 5,281,097 AGeneral Electric Company · 1994
- Stable blade vibration damper for gas turbine engine79US 5,478,207 AGeneral Electric Company · 1995
- Deflector for controlling entry of cooling air leakage into the gaspath of a gas turbine engine76US 6,077,035 APratt & Whitney Canada Corp. · 2000
- Composite fan platform71US 6,217,283 B1General Electric Company · 2001