F05D 2240/121
Related to the leading edge of a stator vane
Official title: related to the leading edge of a stator vane
F05D2240/121 (Related to the leading edge of a stator vane) appears on 504 US grants and 540 published applications in this corpus.
Search patents in F05D- Granted patents
- 504
- Published applications
- 540
- Assignees
- 106
- Inventors
- 1,039
- Latest grant
- 15 Sep 2026
Filings by year
| Year | Granted patents | Published applications |
|---|---|---|
| 1977 | 1 | 0 |
| 1978 | 0 | 0 |
| 1979 | 0 | 0 |
| 1980 | 0 | 0 |
| 1981 | 0 | 0 |
| 1982 | 1 | 0 |
| 1983 | 0 | 0 |
| 1984 | 0 | 0 |
| 1985 | 0 | 0 |
| 1986 | 1 | 0 |
| 1987 | 0 | 0 |
| 1988 | 0 | 0 |
| 1989 | 0 | 0 |
| 1990 | 0 | 0 |
| 1991 | 0 | 0 |
| 1992 | 0 | 0 |
| 1993 | 2 | 0 |
| 1994 | 0 | 0 |
| 1995 | 0 | 0 |
| 1996 | 4 | 0 |
| 1997 | 1 | 0 |
| 1998 | 1 | 0 |
| 1999 | 2 | 0 |
| 2000 | 6 | 0 |
| 2001 | 3 | 2 |
| 2002 | 3 | 1 |
| 2003 | 1 | 1 |
| 2004 | 0 | 1 |
| 2005 | 1 | 5 |
| 2006 | 3 | 4 |
| 2007 | 5 | 9 |
| 2008 | 5 | 8 |
| 2009 | 7 | 21 |
| 2010 | 13 | 19 |
| 2011 | 11 | 10 |
| 2012 | 21 | 14 |
| 2013 | 13 | 16 |
| 2014 | 10 | 15 |
| 2015 | 19 | 27 |
| 2016 | 16 | 42 |
| 2017 | 19 | 38 |
| 2018 | 23 | 44 |
| 2019 | 41 | 46 |
| 2020 | 68 | 57 |
| 2021 | 36 | 28 |
| 2022 | 40 | 21 |
| 2023 | 43 | 46 |
| 2024 | 42 | 26 |
| 2025 | 31 | 19 |
| 2026 | 11 | 20 |
By publication year. Applications have been published since 2001. 2026 runs to 8 Oct.
Recent patents
- Metal coupon with porous stress-relief section and component with same15 Sep 2026US 12,735,986 B2GE Infrastructure Technology LLC
- Aircraft engine with stator having varying pitch21 Jul 2026US 12,687,114 B2Pratt & Whitney Canada Corp.
- System and method for contouring edges of airfoils14 Jul 2026US 12,678,899 B2General Electric Company
- Turbine nozzle alignment with combustor of gas turbine engines14 Jul 2026US 12,680,460 B1General Electric Company
- Fan inlet case strut16 Jun 2026US 12,655,766 B1Rtx Corporation
- Variable-pitch vane for an unducted aeronautical thruster1 Oct 2026US 2026/0298260 A1Safran Aircraft Engines
- Turbine engine with composite airfoils13 Aug 2026US 2026/0235036 A1General Electric Company
- Leading edge plating on low pressure compressor vane for weight and strength optimization6 Aug 2026US 2026/0226834 A1Pratt & Whitney Canada Corp.
- Gas Turbine Engine with Forward Swept Outlet Guide Vanes30 Jul 2026US 2026/0218667 A1General Electric Company
- Fixed radial inlet guide vanes configured to direct exhaust to a turbine25 Jun 2026US 2026/0176977 A1Garrett Transportation I Inc.
Most cited
By later US patents
- Coolable airfoil for a gas turbine engine160US 6,099,251 AUnited Technologies Corporation · 2000
- Airfoil with dual source cooling72US 5,498,126 AUnited Technologies Corporation · 1996
- Low noise permeable airfoil71US 6,139,259 AGeneral Electric Company · 2000
- Hollow airfoil for a gas turbine engine62US 6,164,912 AUnited Technologies Corporation · 2000
- Advanced booster rotor blade60US 7,967,571 B2General Electric Company · 2011