Gas turbine engine sensor system with static pressure sensors
US11867070B1 · kind B1 · utility
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4References
19Claims
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Assignee
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Key dates
| Filing date | Jul 29, 2022 |
| Grant date | Jan 9, 2024 |
| Priority date | — |
| Expiry date | Jul 29, 2042 |
Classification
- Technology area (CPC —)General
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.