![Performance analysis of an aero engine with inter-stage turbine burner | The Aeronautical Journal | Cambridge Core Performance analysis of an aero engine with inter-stage turbine burner | The Aeronautical Journal | Cambridge Core](https://static.cambridge.org/binary/version/id/urn:cambridge.org:id:binary:20171113091739170-0244:S0001924017000938:S0001924017000938_fig3g.jpeg?pub-status=live)
Performance analysis of an aero engine with inter-stage turbine burner | The Aeronautical Journal | Cambridge Core
![Compressor Areas For High Overall Pressure Ratio Gas Turbine Engine - diagram, schematic, and image 01 Compressor Areas For High Overall Pressure Ratio Gas Turbine Engine - diagram, schematic, and image 01](https://www.patentsencyclopedia.com/img/20150252723_01.png)
Compressor Areas For High Overall Pressure Ratio Gas Turbine Engine - diagram, schematic, and image 01
How to calculate the overall pressure ratio in compressors in a gas turbine, especially with jet engines that has dual/twin spool arrangement - Quora
![SOLVED: Air at 10 bar enters a two-stage turbine with reheat operating at steady state. The overall pressure ratio across the stages is 10. Reheat occurs at the pressure that maximizes total SOLVED: Air at 10 bar enters a two-stage turbine with reheat operating at steady state. The overall pressure ratio across the stages is 10. Reheat occurs at the pressure that maximizes total](https://cdn.numerade.com/previews/ddc81021-a942-463c-8f2e-55018ebd526c_large.jpg)