F05D 2250/132
Hexagonal
Official title: hexagonal
F05D2250/132 (Hexagonal) appears on 67 US grants and 90 published applications in this corpus.
Search patents in F05D- Granted patents
- 67
- Published applications
- 90
- Assignees
- 41
- Inventors
- 220
- Latest grant
- 14 Apr 2026
Filings by year
| Year | Granted patents | Published applications |
|---|---|---|
| 1994 | 1 | 0 |
| 1995 | 0 | 0 |
| 1996 | 0 | 0 |
| 1997 | 0 | 0 |
| 1998 | 0 | 0 |
| 1999 | 0 | 0 |
| 2000 | 0 | 0 |
| 2001 | 0 | 0 |
| 2002 | 0 | 0 |
| 2003 | 0 | 0 |
| 2004 | 0 | 0 |
| 2005 | 0 | 1 |
| 2006 | 1 | 1 |
| 2007 | 0 | 0 |
| 2008 | 1 | 2 |
| 2009 | 0 | 1 |
| 2010 | 1 | 2 |
| 2011 | 1 | 2 |
| 2012 | 0 | 3 |
| 2013 | 1 | 0 |
| 2014 | 3 | 3 |
| 2015 | 2 | 2 |
| 2016 | 2 | 9 |
| 2017 | 1 | 5 |
| 2018 | 2 | 12 |
| 2019 | 10 | 11 |
| 2020 | 7 | 8 |
| 2021 | 9 | 3 |
| 2022 | 3 | 5 |
| 2023 | 6 | 8 |
| 2024 | 6 | 7 |
| 2025 | 8 | 3 |
| 2026 | 2 | 2 |
By publication year. Applications have been published since 2001. 2026 runs to 8 Oct.
Recent patents
- Radially captured in situ balancing masses for aircraft powerplant14 Apr 2026US 12,601,263 B1Pratt & Whitney Canada Corp.
- Element and method for compensation of tolerances and/or gap widths of a device and engine, assembly method for a shaft/hub connection13 Jan 2026US 12,523,160 B2Universität der Bundeswehr München
- Composite component having an additively printed inner portion11 Nov 2025US 12,467,369 B2General Electric Company
- Substrate edge configurations for ceramic coatings4 Nov 2025US 12,460,555 B2Rtx Corporation
- Propeller shaft assembly for aircraft engine21 Oct 2025US 12,448,998 B2Pratt & Whitney Canada Corp.
- Airfoil for a turbine engine27 Aug 2026US 2026/0251067 A1General Electric Company
- Radially captured in situ balancing masses for aircraft powerplant28 May 2026US 2026/0146536 A1Pratt & Whitney Canada Corp.
- Max phase-gold composites and methods for making the same12 Jun 2025US 2025/0188570 A1
- Composite component having an additively printed inner portion27 Feb 2025US 2025/0067186 A1General Electric Company
- Turbine engine support structure with airflow ports2 Jan 2025US 2025/0003590 A1Rtx Corporation
Most cited
By later US patents
- Flow laminarizing device37US 7,089,963 B22006
- Ice protection system for a multi-segment aircraft component19US 7,837,150 B2Goodrich Corporation · 2010
- Component lock for a gas turbine engine19US 8,840,375 B2United Technologies Corporation · 2014
- Acoustic liner for gas turbine engine components14US 10,174,675 B2General Electric Company · 2019
- Hexagonal cluster nozzle for a rocket engine14US 5,343,698 AUnited Technologies Corporation · 1994