Abstract
The need for a small bleed-off gas-turbine engine arose when the large turbojet and turboprop aircraft engines were introduced into military service. The problem of starting turbojet and turboprop aircraft engines became more acute as the starting power requirements began to exceed the practical weight and size limits of electric starters. As a result, development of a pneumatic starting system was undertaken. To make the low-pressure air starter practical, it was necessary to have a small, lightweight source of compressed air. The small gas-turbine bleed-off compressor unit was developed for this purpose. This paper describes the development procedure and details of this type engine as it now stands. So far only a few thousand units have been produced, but cost reductions are expected as use for these small gas-turbine engines increases.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
