F01D 5/081
Cooling fluid being directed on the side of the rotor disc or
Official title: {Cooling fluid being directed on the side of the rotor disc or at the roots of the blades (F01D5/087 takes precedence)}
F01D5/081 (Cooling fluid being directed on the side of the rotor disc or) appears on 1,038 US grants and 963 published applications in this corpus.
Search patents in F01D- Granted patents
- 1,038
- Published applications
- 963
- Assignees
- 123
- Inventors
- 1,901
- Latest grant
- 11 Aug 2026
Filings by year
| Year | Granted patents | Published applications |
|---|---|---|
| 1976 | 6 | 0 |
| 1977 | 3 | 0 |
| 1978 | 2 | 0 |
| 1979 | 1 | 0 |
| 1980 | 3 | 0 |
| 1981 | 3 | 0 |
| 1982 | 2 | 0 |
| 1983 | 1 | 0 |
| 1984 | 8 | 0 |
| 1985 | 4 | 0 |
| 1986 | 3 | 0 |
| 1987 | 10 | 0 |
| 1988 | 6 | 0 |
| 1989 | 13 | 0 |
| 1990 | 2 | 0 |
| 1991 | 2 | 0 |
| 1992 | 8 | 0 |
| 1993 | 12 | 0 |
| 1994 | 8 | 0 |
| 1995 | 6 | 0 |
| 1996 | 7 | 0 |
| 1997 | 7 | 0 |
| 1998 | 10 | 0 |
| 1999 | 13 | 0 |
| 2000 | 13 | 0 |
| 2001 | 17 | 5 |
| 2002 | 27 | 19 |
| 2003 | 17 | 15 |
| 2004 | 14 | 21 |
| 2005 | 13 | 30 |
| 2006 | 26 | 30 |
| 2007 | 20 | 31 |
| 2008 | 18 | 17 |
| 2009 | 19 | 34 |
| 2010 | 16 | 32 |
| 2011 | 22 | 44 |
| 2012 | 32 | 64 |
| 2013 | 36 | 54 |
| 2014 | 48 | 43 |
| 2015 | 55 | 51 |
| 2016 | 33 | 98 |
| 2017 | 52 | 84 |
| 2018 | 73 | 62 |
| 2019 | 69 | 52 |
| 2020 | 92 | 40 |
| 2021 | 48 | 45 |
| 2022 | 53 | 23 |
| 2023 | 33 | 23 |
| 2024 | 18 | 22 |
| 2025 | 20 | 16 |
| 2026 | 14 | 8 |
By publication year. Applications have been published since 2001. 2026 runs to 8 Oct.
Subgroups
Granted patents
Recent patents
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- Gas turbine engine with improved high pressure compressor leakage path guide structure4 Aug 2026US 12,698,901 B2Rtx Corporation
- Cooling-air injection casing for a turbomachine turbine14 Jul 2026US 12,680,462 B2Safran Aircraft Engines
- Air injection casing for a turbomachine30 Jun 2026US 12,669,059 B2Safran Aircraft Engines
- Air system for aircraft powerplant23 Jun 2026US 12,662,963 B1Rtx Corporation
- Expander and thermodynamic cycle using the expander17 Sep 2026US 2026/0275871 A1Nuovo Pignone Tecnologie Srl
- Valve for an aircraft turbine engine2 Jul 2026US 2026/0185626 A1Safran Aircraft Engines
- Air injection casing for a turbomachine23 Apr 2026US 2026/0110251 A1Safran Aircraft Engines
- Turbine Engine Rotor Blade With Contoured Pocket Surface(S)2 Apr 2026US 2026/0092530 A1Pratt & Whitney Canada Corp.
- Center Tie Rotor Annular Seal12 Mar 2026US 2026/0071551 A1Rtx Corporation
Most cited
By later US patents
- Compressor rotor cooling system for a gas turbine125US 5,685,158 AGeneral Electric Company · 1997
- Modulated turbine cooling system104US 6,050,079 AGeneral Electric Company · 2000
- Turbine disk interstage seal system96US 5,236,302 AGeneral Electric Company · 1993
- Gas turbine engine temperature modulated cooling flow96US 8,307,662 B2General Electric Company · 2012
- Turbine disk cooling system94US 5,472,313 AGeneral Electric Company · 1995