Air recuperated engine with air reinjection
US-12331679-B2 · Jun 17, 2025 · US
the compressor having concentric stages
the compressor having concentric stages · Cooperative Patent Classification (CPC)
Engines, pumps, lighting, heating, and mechanical systems.
Related technology areas
Mapped technology topics for this CPC code.
| Metric | Value |
|---|---|
| CPC code | F02C3/064 |
| Official title | {the compressor having concentric stages} |
| Display label | the compressor having concentric stages |
| Total patents | 49 |
Filing trend
Year-over-year patent counts classified under this CPC code.
Filing activity over the last five years is declining.
| Year | Patents |
|---|---|
| 2015 | 2 |
| 2016 | 3 |
| 2017 | 4 |
| 2018 | 6 |
| 2019 | 4 |
| 2020 | 6 |
| 2021 | 4 |
| 2022 | 5 |
| 2023 | 4 |
| 2024 | 9 |
| 2025 | 2 |
Representative patents
Representative publications under this CPC code from precomputed stats, or recent filings when stats are unavailable.
Turbine engine core and bypass flows
US-2025035037-A1 · Jan 30, 2025 · US
Turbine engine core and bypass flows having a defined fan-turbine radial distance
US-12163464-B2 · Dec 10, 2024 · US
Air recuperated engine with air reinjection
US-2024401523-A1 · Dec 5, 2024 · US
Compressor bleed pressure recovery
US-12146423-B2 · Nov 19, 2024 · US
Air recuperated engine with air reinjection
US-12078102-B2 · Sep 3, 2024 · US
Compressor bleed pressure recovery
US-2024229664-A1 · Jul 11, 2024 · US
Gas turbine engine with third stream
US-2024159191-A1 · May 16, 2024 · US
Air recuperated engine with air reinjection
US-2024102417-A1 · Mar 28, 2024 · US
Turbine circumferential dovetail leakage reduction
US-11920498-B2 · Mar 5, 2024 · US
Adjustable guide vane with convexly shaped, radially inner storage section for a gas turbine, in particular an aircraft gas turbine
US-11892012-B2 · Feb 6, 2024 · US
Operability geared turbofan engine including compressor section variable guide vanes
US-11781490-B2 · Oct 10, 2023 · US
Adjustable guide vane with convexly shaped, radially inner storage section for a gas turbine, in particular an aircraft gas turbine
US-2023235752-A1 · Jul 27, 2023 · US
Turbine circumferential dovetail leakage reduction
US-2023037224-A1 · Feb 2, 2023 · US
Turbine engine core and bypass flows
US-2023028367-A1 · Jan 26, 2023 · US
Turbine circumferential dovetail leakage reduction
US-11486261-B2 · Nov 1, 2022 · US
Multi-engine architecture with linkages to multiple spools
US-11415044-B2 · Aug 16, 2022 · US
Large-scale bypass fan configuration for turbine engine core and bypass flows
US-11339713-B2 · May 24, 2022 · US
Operability geared turbofan engine including compressor section variable guide vanes
US-2022145807-A1 · May 12, 2022 · US
Operability geared turbofan engine including compressor section variable guide vanes
US-11280271-B2 · Mar 22, 2022 · US
Frequently asked questions
Answers are generated from the same data shown on this page.
- What is CPC F02C3/064?
- CPC F02C3/064 is the Cooperative Patent Classification code for “the compressor having concentric stages.”
- How many patents are filed under CPC F02C3/064 (the compressor having concentric stages)?
- Our database includes 49 publications tagged with this CPC code.
- Is patent activity under CPC F02C3/064 growing?
- Publication counts under this code: 9 in 2024 vs 2 in 2025 (latest complete years).