F01D 5/3092
Protective layers between blade root and rotor disc surfaces
Official title: {Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers (F01D5/288 takes precedence)}
F01D5/3092 (Protective layers between blade root and rotor disc surfaces) appears on 228 US grants and 239 published applications in this corpus.
Search patents in F01D- Granted patents
- 228
- Published applications
- 239
- Assignees
- 62
- Inventors
- 544
- Latest grant
- 24 Feb 2026
Filings by year
| Year | Granted patents | Published applications |
|---|---|---|
| 1977 | 2 | 0 |
| 1978 | 1 | 0 |
| 1979 | 1 | 0 |
| 1980 | 1 | 0 |
| 1981 | 0 | 0 |
| 1982 | 0 | 0 |
| 1983 | 2 | 0 |
| 1984 | 1 | 0 |
| 1985 | 1 | 0 |
| 1986 | 0 | 0 |
| 1987 | 0 | 0 |
| 1988 | 1 | 0 |
| 1989 | 1 | 0 |
| 1990 | 2 | 0 |
| 1991 | 0 | 0 |
| 1992 | 2 | 0 |
| 1993 | 1 | 0 |
| 1994 | 4 | 0 |
| 1995 | 1 | 0 |
| 1996 | 2 | 0 |
| 1997 | 0 | 0 |
| 1998 | 3 | 0 |
| 1999 | 3 | 0 |
| 2000 | 4 | 0 |
| 2001 | 3 | 0 |
| 2002 | 3 | 2 |
| 2003 | 1 | 2 |
| 2004 | 5 | 5 |
| 2005 | 2 | 4 |
| 2006 | 1 | 4 |
| 2007 | 4 | 6 |
| 2008 | 1 | 6 |
| 2009 | 1 | 8 |
| 2010 | 1 | 8 |
| 2011 | 6 | 11 |
| 2012 | 8 | 16 |
| 2013 | 9 | 13 |
| 2014 | 12 | 19 |
| 2015 | 11 | 19 |
| 2016 | 14 | 33 |
| 2017 | 18 | 8 |
| 2018 | 14 | 14 |
| 2019 | 21 | 4 |
| 2020 | 10 | 13 |
| 2021 | 9 | 8 |
| 2022 | 10 | 5 |
| 2023 | 3 | 6 |
| 2024 | 13 | 12 |
| 2025 | 14 | 11 |
| 2026 | 1 | 2 |
By publication year. Applications have been published since 2001. 2026 runs to 8 Oct.
Recent patents
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- Protection element for a compressor drum and method for repairing a compressor drum30 Dec 2025US 12,509,994 B2Safran Aircraft Engines
- Foil, assembly for a turbomachine rotor and turbomachine11 Nov 2025US 12,467,373 B2Safran Aircraft Engines
- Composite airfoil assembly having a composite airfoil and spar21 Oct 2025US 12,448,892 B2General Electric Company
- Method for turbine blade and assembly with dovetail arrangement for enlarged rotor groove7 Oct 2025US 12,435,637 B2GE Infrastructure Technology LLC
- Shape memory alloy under-root fan blade spacer16 Jul 2026US 2026/0201805 A1Rtx Corporation
- Turbine engine with a blade assembly having a dovetail16 Apr 2026US 2026/0103990 A1General Electric Company
- Device for axially retaining moving blades of an lp turbine in the slots of a rotor disc of the lp turbine and method for assembling said moving blades6 Nov 2025US 2025/0341167 A1Safran Aircraft Engines
- Wear pad for root of fan blade30 Oct 2025US 2025/0334053 A1Rtx Corporation
- Composite airfoil assembly having a composite airfoil and spar14 Aug 2025US 2025/0257660 A1General Electric Company
Most cited
By later US patents
- Ceramic airfoil91US 6,000,906 AAlliedSignal Inc. · 1999
- Coated article and method for inhibiting frictional wear between mating titanium alloy substrates in a gas turbine engine90US 6,158,963 AUnited Technologies Corporation · 2000
- Compliant interface for ceramic turbine blades78US 4,417,854 ARockwell International Corporation · 1983
- Process for producing fiber reinforced composite74US 5,876,659 AHitachi, Ltd. · 1999
- Turbine blade wear protection system with multilayer shim64US 5,160,243 AGeneral Electric Company · 1992