F01D 9/023
Transition ducts between combustor cans and first stage of the turbine in
Official title: {Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings}
F01D9/023 (Transition ducts between combustor cans and first stage of the turbine in) appears on 926 US grants and 1,019 published applications in this corpus.
Search patents in F01D- Granted patents
- 926
- Published applications
- 1,019
- Assignees
- 134
- Inventors
- 1,761
- Latest grant
- 22 Sep 2026
Filings by year
| Year | Granted patents | Published applications |
|---|---|---|
| 1976 | 2 | 0 |
| 1977 | 1 | 0 |
| 1978 | 0 | 0 |
| 1979 | 1 | 0 |
| 1980 | 2 | 0 |
| 1981 | 5 | 0 |
| 1982 | 0 | 0 |
| 1983 | 4 | 0 |
| 1984 | 3 | 0 |
| 1985 | 1 | 0 |
| 1986 | 1 | 0 |
| 1987 | 3 | 0 |
| 1988 | 3 | 0 |
| 1989 | 4 | 0 |
| 1990 | 1 | 0 |
| 1991 | 1 | 0 |
| 1992 | 4 | 0 |
| 1993 | 5 | 0 |
| 1994 | 3 | 0 |
| 1995 | 11 | 0 |
| 1996 | 5 | 0 |
| 1997 | 2 | 0 |
| 1998 | 4 | 0 |
| 1999 | 5 | 0 |
| 2000 | 6 | 0 |
| 2001 | 8 | 3 |
| 2002 | 16 | 8 |
| 2003 | 14 | 11 |
| 2004 | 9 | 11 |
| 2005 | 8 | 23 |
| 2006 | 13 | 18 |
| 2007 | 19 | 22 |
| 2008 | 4 | 19 |
| 2009 | 11 | 34 |
| 2010 | 16 | 54 |
| 2011 | 27 | 42 |
| 2012 | 41 | 69 |
| 2013 | 36 | 58 |
| 2014 | 41 | 71 |
| 2015 | 54 | 54 |
| 2016 | 60 | 75 |
| 2017 | 40 | 77 |
| 2018 | 54 | 94 |
| 2019 | 64 | 59 |
| 2020 | 92 | 67 |
| 2021 | 67 | 29 |
| 2022 | 49 | 36 |
| 2023 | 35 | 35 |
| 2024 | 37 | 17 |
| 2025 | 18 | 21 |
| 2026 | 16 | 12 |
By publication year. Applications have been published since 2001. 2026 runs to 8 Oct.
Recent patents
- Transition duct for gas turbine engine22 Sep 2026US 12,742,396 B2Siemens Energy Global GmbH & Co. KG
- Gas turbine engine with improved high pressure compressor leakage path guide structure4 Aug 2026US 12,698,901 B2Rtx Corporation
- Combustor-vane interface feather seal23 Jun 2026US 12,662,945 B2Rtx Corporation
- Method for repairing vane of gas turbine engine16 Jun 2026US 12,655,765 B1Rtx Corporation
- Gas turbine combustor and gas turbine26 May 2026US 12,638,182 B2Mitsubishi Heavy Industries, Ltd.
- Double-section spring element6 Aug 2026US 2026/0226986 A1Rolls-Royce Deutschland Ltd & Co KG
- Targeted location correction of thermal barrier coated diffusers30 Jul 2026US 2026/0216829 A1Rtx Corporation
- Combustor with additively manufactured combustor body having cooling path with inlet at aft frame16 Jul 2026US 2026/0201806 A1GE Vernova Infrastructure Technology LLC
- Duct and gas turbine16 Jul 2026US 2026/0201820 A1Mitsubishi Heavy Industries, Ltd.
- Combustor with additively manufactured combustor body having impingement cooling of combustion liner near aft frame16 Jul 2026US 2026/0202056 A1GE Vernova Infrastructure Technology LLC
Most cited
By later US patents
- Impingement cooled transition duct153US 4,719,748 AGeneral Electric Company · 1988
- Integral aft seal for turbine applications100US 6,450,762 B1General Electric Company · 2002
- Self-accommodating brush seal for gas turbine combustor98US 5,400,586 AGeneral Electric Company · 1995
- Aft mounting system for combustion transition duct members93US 4,422,288 AGeneral Electric Company · 1983
- Combustor-turbine nozzle interconnection92US 3,965,066 AGeneral Electric Company · 1976