F05D 2220/3216
For a special compressor stage
Official title: for a special compressor stage
F05D2220/3216 (For a special compressor stage) appears on 334 US grants and 354 published applications in this corpus.
Search patents in F05D- Granted patents
- 334
- Published applications
- 354
- Assignees
- 68
- Inventors
- 739
- Latest grant
- 14 Jul 2026
Filings by year
| Year | Granted patents | Published applications |
|---|---|---|
| 1997 | 1 | 0 |
| 1998 | 0 | 0 |
| 1999 | 0 | 0 |
| 2000 | 0 | 0 |
| 2001 | 0 | 0 |
| 2002 | 0 | 0 |
| 2003 | 0 | 0 |
| 2004 | 1 | 0 |
| 2005 | 0 | 0 |
| 2006 | 0 | 0 |
| 2007 | 0 | 0 |
| 2008 | 0 | 5 |
| 2009 | 4 | 5 |
| 2010 | 2 | 2 |
| 2011 | 1 | 2 |
| 2012 | 4 | 5 |
| 2013 | 3 | 9 |
| 2014 | 6 | 12 |
| 2015 | 2 | 14 |
| 2016 | 7 | 33 |
| 2017 | 9 | 21 |
| 2018 | 15 | 41 |
| 2019 | 42 | 24 |
| 2020 | 61 | 63 |
| 2021 | 43 | 36 |
| 2022 | 53 | 16 |
| 2023 | 21 | 26 |
| 2024 | 26 | 17 |
| 2025 | 20 | 18 |
| 2026 | 13 | 5 |
By publication year. Applications have been published since 2001. 2026 runs to 8 Oct.
Subgroups
Granted patents
Recent patents
- Forward load reduction structures for aft-most stages of high pressure compressors14 Jul 2026US 12,680,557 B2General Electric Company
- Gas turbine engine2 Jun 2026US 12,644,386 B2General Electric Company
- Impeller containment system21 Apr 2026US 12,607,201 B2Pratt & Whitney Canada Corp.
- Aircraft engine impeller with exducer shroud forward sweep31 Mar 2026US 12,590,590 B2Pratt & Whitney Canada Corp.
- Hybrid shroud impeller10 Mar 2026US 12,571,409 B2Rtx Corporation
- Compressor bleed slot diffuser30 Jul 2026US 2026/0218652 A1Pratt & Whitney Canada Corp.
- More compact aircraft propulsion system23 Jul 2026US 2026/0210297 A1Safran Aircraft Engines
- Coating for Aluminum Alloy Aerostructures2 Jul 2026US 2026/0185451 A1Rtx Corporation
- Hybrid shroud impeller25 Jun 2026US 2026/0177077 A1Rtx Corporation
- Gas turbine engine compression system with core compressor pressure ratio30 Apr 2026US 2026/0116550 A1ROLLS-ROYC plc
Most cited
By later US patents
- Multiple staged compressor with last stage airfoil cooling57US 8,858,161 B1Florida Turbine Technologies, Inc. · 2014
- Compressor blade having a ratio of leading edge sweep to leading edge dihedral in a range of 1:1 to 3:1 along the radially outer portion55US 8,147,207 B2Siemens Energy, Inc. · 2012
- Airfoil shape for a compressor46US 7,494,323 B2General Electric Company · 2009
- Airfoil shape for a compressor45US 7,510,378 B2General Electric Company · 2009
- Airfoil shape for a compressor43US 7,520,729 B2General Electric Company · 2009