F02C 3/08
The compressor comprising at least one radial stage
Official title: the compressor comprising at least one radial stage (F02C3/10 takes precedence)
F02C3/08 (The compressor comprising at least one radial stage) appears on 262 US grants and 246 published applications in this corpus.
Search patents in F02C- Granted patents
- 262
- Published applications
- 246
- Assignees
- 91
- Inventors
- 506
- Latest grant
- 25 Aug 2026
Filings by year
| Year | Granted patents | Published applications |
|---|---|---|
| 1976 | 2 | 0 |
| 1977 | 7 | 0 |
| 1978 | 2 | 0 |
| 1979 | 1 | 0 |
| 1980 | 1 | 0 |
| 1981 | 0 | 0 |
| 1982 | 0 | 0 |
| 1983 | 0 | 0 |
| 1984 | 1 | 0 |
| 1985 | 0 | 0 |
| 1986 | 2 | 0 |
| 1987 | 1 | 0 |
| 1988 | 0 | 0 |
| 1989 | 4 | 0 |
| 1990 | 3 | 0 |
| 1991 | 2 | 0 |
| 1992 | 5 | 0 |
| 1993 | 5 | 0 |
| 1994 | 3 | 0 |
| 1995 | 1 | 0 |
| 1996 | 2 | 0 |
| 1997 | 3 | 0 |
| 1998 | 3 | 0 |
| 1999 | 1 | 0 |
| 2000 | 0 | 0 |
| 2001 | 4 | 1 |
| 2002 | 2 | 1 |
| 2003 | 4 | 6 |
| 2004 | 1 | 7 |
| 2005 | 4 | 5 |
| 2006 | 2 | 3 |
| 2007 | 1 | 8 |
| 2008 | 2 | 12 |
| 2009 | 2 | 7 |
| 2010 | 4 | 8 |
| 2011 | 13 | 6 |
| 2012 | 9 | 6 |
| 2013 | 3 | 7 |
| 2014 | 5 | 14 |
| 2015 | 6 | 4 |
| 2016 | 8 | 8 |
| 2017 | 10 | 14 |
| 2018 | 5 | 15 |
| 2019 | 15 | 12 |
| 2020 | 20 | 26 |
| 2021 | 19 | 12 |
| 2022 | 21 | 18 |
| 2023 | 16 | 11 |
| 2024 | 15 | 11 |
| 2025 | 11 | 12 |
| 2026 | 11 | 12 |
By publication year. Applications have been published since 2001. 2026 runs to 8 Oct.
Subgroups
Granted patents
Recent patents
- Aircraft gas turbine engine impeller with a trailing edge that is non-linear or angled or irregularly-shaped25 Aug 2026US 12,716,424 B2Pratt & Whitney Canada Corp.
- Gas turbine engine30 Jun 2026US 12,669,084 B2GE Avio S. r. l.
- Axial-centrifugal contra-rotating light weight, compact compression system23 Jun 2026US 12,662,960 B2Indian Institute of Technology Kharagpur
- Impeller backface cooled P3 passage through diffuser/reducing high temp exposure of cooled air16 Jun 2026US 12,655,796 B1Pratt & Whitney Canada Corp.
- Methods and apparatus to provide cross-diffuser bleed5 May 2026US 12,618,362 B2General Electric Company
- Gas turbine engine8 Oct 2026US 2026/0309076 A1GE Avio S. r. l.
- Compressor bleed slot diffuser30 Jul 2026US 2026/0218652 A1Pratt & Whitney Canada Corp.
- Centrifugal compressor diffuser30 Jul 2026US 2026/0218724 A1Pratt & Whitney Canada Corp.
- Methods and apparatus to provide cross-diffuser bleed2 Jul 2026US 2026/0185480 A1General Electric Company
- Cooling nozzle vanes of a turbine engine18 Jun 2026US 2026/0168385 A1Rtx Corporation
Most cited
By later US patents
- High efficiency, twin spool, radial-high pressure, gas turbine engine139US 5,081,832 A1992
- Low volumetric compression ratio integrated turbo-compound rotary engine85US 7,775,044 B2Pratt & Whitney Canada Corp. · 2010
- Integrated bypass turbojet engines for air craft and other vehicles78US 6,966,174 B22005
- Gas turbine engine/load compressor power plants64US 4,627,234 ASundstrand Corporation · 1986
- Turbine cooling air from a centrifugal compressor61US 8,087,249 B2General Electric Company · 2012