F05D 2240/80
Platforms for stationary or moving blades
F05D2240/80 (Platforms for stationary or moving blades) appears on 1,735 US grants and 1,803 published applications in this corpus.
Search patents in F05D- Granted patents
- 1,735
- Published applications
- 1,803
- Assignees
- 145
- Inventors
- 2,698
- Latest grant
- 6 Oct 2026
Filings by year
| Year | Granted patents | Published applications |
|---|---|---|
| 1976 | 3 | 0 |
| 1977 | 5 | 0 |
| 1978 | 2 | 0 |
| 1979 | 3 | 0 |
| 1980 | 5 | 0 |
| 1981 | 5 | 0 |
| 1982 | 3 | 0 |
| 1983 | 0 | 0 |
| 1984 | 0 | 0 |
| 1985 | 2 | 0 |
| 1986 | 5 | 0 |
| 1987 | 5 | 0 |
| 1988 | 3 | 0 |
| 1989 | 1 | 0 |
| 1990 | 5 | 0 |
| 1991 | 0 | 0 |
| 1992 | 5 | 0 |
| 1993 | 3 | 0 |
| 1994 | 7 | 0 |
| 1995 | 7 | 0 |
| 1996 | 6 | 0 |
| 1997 | 4 | 0 |
| 1998 | 14 | 0 |
| 1999 | 8 | 0 |
| 2000 | 20 | 0 |
| 2001 | 18 | 9 |
| 2002 | 34 | 18 |
| 2003 | 19 | 11 |
| 2004 | 17 | 27 |
| 2005 | 16 | 33 |
| 2006 | 31 | 28 |
| 2007 | 20 | 39 |
| 2008 | 14 | 27 |
| 2009 | 27 | 36 |
| 2010 | 21 | 47 |
| 2011 | 22 | 53 |
| 2012 | 51 | 58 |
| 2013 | 50 | 97 |
| 2014 | 76 | 65 |
| 2015 | 52 | 68 |
| 2016 | 51 | 216 |
| 2017 | 62 | 135 |
| 2018 | 131 | 133 |
| 2019 | 162 | 134 |
| 2020 | 190 | 152 |
| 2021 | 154 | 99 |
| 2022 | 132 | 68 |
| 2023 | 73 | 76 |
| 2024 | 85 | 64 |
| 2025 | 68 | 60 |
| 2026 | 38 | 50 |
By publication year. Applications have been published since 2001. 2026 runs to 8 Oct.
Subgroups
Granted patents
Recent patents
- Turbine engine with a blade assembly having a set of cooling conduits6 Oct 2026US 12,753,696 B2General Electric Company
- Metal coupon with porous stress-relief section and component with same15 Sep 2026US 12,735,986 B2GE Infrastructure Technology LLC
- Turbine blade with boomerang shaped wall cooling passages25 Aug 2026US 12,716,359 B2Rtx Corporation
- Axial compressor integrated bladed rotor airfoil design scheme18 Aug 2026US 12,709,986 B1Pratt & Whitney Canada Corp.
- Annulus contouring4 Aug 2026US 12,698,713 B2MTU Aero Engines AG
- Assembly for maintaining and retaining a gas turbine engine component8 Oct 2026US 2026/0309037 A1Rtx Corporation
- Guide Vane Segment17 Sep 2026US 2026/0275876 A1MTU Aero Engines AG
- Gas turbine engine rotor stage with rotor blade damper arrangement10 Sep 2026US 2026/0266185 A1Rtx Corporation
- Turbine blade and gas turbine27 Aug 2026US 2026/0251068 A1Mitsubishi Heavy Industries, Ltd.
- Rotor assembly with independent platforms and method for assembling such a rotor20 Aug 2026US 2026/0243168 A1
Most cited
By later US patents
- Air-cooled turbine blade115US 5,813,835 AThe United States of America as represented by the Secretary of the Air Force · 1998
- Method of fabricating film cooling slot in a hollow airfoil113US 4,672,727 AUnited Technologies Corporation · 1987
- Multiple-impingement cooled structure100US 4,573,865 AGeneral Electric Company · 1986
- Rotor blade with cooled integral platform96US 5,382,135 AUnited Technologies Corporation · 1995
- Cooled turbine blade and combined cycle power plant having gas turbine with this cooled turbine blade93US 5,120,192 AKabushiki Kaisha Toshiba · 1992