F01D 11/14
Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
Official title: Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing (rotors with blades adjustable in operation F01D7/00)
F01D11/14 (Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing) appears on 1,433 US grants and 1,402 published applications in this corpus.
Search patents in F01D- Granted patents
- 1,433
- Published applications
- 1,402
- Assignees
- 182
- Inventors
- 2,558
- Latest grant
- 22 Sep 2026
Filings by year
| Year | Granted patents | Published applications |
|---|---|---|
| 1976 | 4 | 0 |
| 1977 | 5 | 0 |
| 1978 | 4 | 0 |
| 1979 | 1 | 0 |
| 1980 | 5 | 0 |
| 1981 | 9 | 0 |
| 1982 | 12 | 0 |
| 1983 | 4 | 0 |
| 1984 | 7 | 0 |
| 1985 | 6 | 0 |
| 1986 | 6 | 0 |
| 1987 | 9 | 0 |
| 1988 | 6 | 0 |
| 1989 | 14 | 0 |
| 1990 | 4 | 0 |
| 1991 | 19 | 0 |
| 1992 | 21 | 0 |
| 1993 | 12 | 0 |
| 1994 | 12 | 0 |
| 1995 | 5 | 0 |
| 1996 | 4 | 0 |
| 1997 | 11 | 0 |
| 1998 | 6 | 0 |
| 1999 | 6 | 0 |
| 2000 | 18 | 0 |
| 2001 | 11 | 4 |
| 2002 | 14 | 17 |
| 2003 | 15 | 11 |
| 2004 | 15 | 15 |
| 2005 | 15 | 30 |
| 2006 | 16 | 26 |
| 2007 | 21 | 26 |
| 2008 | 17 | 34 |
| 2009 | 16 | 34 |
| 2010 | 29 | 58 |
| 2011 | 22 | 38 |
| 2012 | 40 | 38 |
| 2013 | 33 | 71 |
| 2014 | 45 | 78 |
| 2015 | 49 | 79 |
| 2016 | 58 | 132 |
| 2017 | 69 | 111 |
| 2018 | 89 | 99 |
| 2019 | 142 | 96 |
| 2020 | 123 | 96 |
| 2021 | 99 | 67 |
| 2022 | 82 | 56 |
| 2023 | 62 | 51 |
| 2024 | 52 | 49 |
| 2025 | 58 | 40 |
| 2026 | 31 | 46 |
By publication year. Applications have been published since 2001. 2026 runs to 8 Oct.
Subgroups
Granted patents
Recent patents
- CMC component with structure for directing cooling air flow22 Sep 2026US 12,742,398 B2Rtx Corporation
- Blade tip clearance sensor and gas turbine including same22 Sep 2026US 12,742,399 B2Doosan Enerbility Co., Ltd.
- Hot gas path segment with seal slot cooling groove1 Sep 2026US 12,723,518 B2GE Infrastructure Technology LLC
- Gas turbine engine with a rotor stage shroud11 Aug 2026US 12,704,081 B1Pratt & Whitney Canada Corp.
- Seal for a wave rotor disk engine14 Jul 2026US 12,680,463 B1The United States of America as represented by the Secretary of the Air Force
- Hot gas path segment with seal slot cooling groove8 Oct 2026US 2026/0309040 A1GE Vernova Infrastructure Technology LLC
- Turbine engine tip clearance control utilizing electric machine8 Oct 2026US 2026/0309046 A1Rtx Corporation
- Microwave Sensing Architecture for Clearance Control System24 Sep 2026US 2026/0286857 A1Rtx Corporation
- Operational Modes of Direct Drive Clearance Control System24 Sep 2026US 2026/0286858 A1Rtx Corporation
- Blade outer air seal (boas) assembly for a gas turbine engine17 Sep 2026US 2026/0275879 A1Rtx Corporation
Most cited
By later US patents
- Ceramic matrix composite component for a gas turbine engine113US 6,758,653 B2Siemens Westinghouse Power Corporation · 2004
- Blade clearance control using high-CTE and low-CTE ring members109US 8,790,067 B2United Technologies Corporation · 2014
- Expansion control ring for a turbine shroud assembly106US 4,251,185 ACaterpillar Tractor Co. · 1981
- Dual cooled shroud93US 5,993,150 AGeneral Electric Company · 1999
- Active clearance control system for a turbomachine92US 4,329,114 AThe United States of America as represented by the Administrator of the National Aeronautics and Space Administration · 1982