Engine bleed air with compressor surge management
US10533501B2 · kind B2 · utility
1Cited by
11References
15Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jun 20, 2016 |
| Grant date | Jan 14, 2020 |
| Priority date | — |
| Expiry date | Dec 21, 2037 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine includes a main compressor section. A booster compressor includes an inlet and an outlet. The inlet receives airflow from the main compressor section and the outlet provides airflow to a pneumatic system. A recirculation passage is between the inlet and the outlet. A flow splitter valve controls airflow between the outlet and the inlet through the recirculation passage for controlling airflow to the pneumatic system based on airflow output from the booster compressor. A bleed air system for a gas turbine engine and a method of controlling engine bleed airflow are also disclosed.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.