Compressor bleed auxiliary turbine
US10578028B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Aug 18, 2015 |
| Grant date | Mar 3, 2020 |
| Priority date | — |
| Expiry date | Oct 5, 2037 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2270/101
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine is provided having a compressor section, a combustion section, and a turbine section. The compressor section includes one or more compressors and the turbine section includes one or more turbines. The one or more compressors and the one or more turbines are each rotatable about a longitudinal centerline of the gas turbine engine. Additionally, a bleed air flowpath is provided extending between an inlet in airflow communication with the compressor section and an outlet. An auxiliary turbine is positioned in airflow communication with the bleed air flowpath for extracting energy from a flow of bleed air through the bleed air flowpath.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.