Gas turbine engine sensor system with static pressure sensors
US11939876B2 · kind B2 · utility
0Cited by
7References
19Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jul 29, 2022 |
| Grant date | Mar 26, 2024 |
| Priority date | — |
| Expiry date | Jul 29, 2042 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2270/80
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A system is provided for an aircraft. This aircraft system includes a gas turbine engine and a sensor system. The gas turbine engine includes an inlet and a compressor section. A flowpath projects radially inward into the gas turbine engine from the inlet and extends through the compressor section. The sensor system includes a plurality of static pressure sensors at least partially within the flowpath. The sensor system is configured to determine a total pressure characteristic within the flowpath using the plurality of static pressure sensors.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.