The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.
The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.
Patent No.:
Date of Patent:
Nov. 30, 2010
Filed:
Feb. 14, 2006
Martyn Richards, Burton-upon-Trent, GB;
Nicholas Howarth, Derby, GB;
Martyn Richards, Burton-upon-Trent, GB;
Nicholas Howarth, Derby, GB;
Rolls-Royce plc, London, GB;
Abstract
Disparities between optimum engine thrust for aircraft operation and power necessary to drive an ancillary machine such an electrical power generator can cause problems within a turbine engine. Clearly, it is necessary to continue developing sufficient electrical power for control and other systems within an aircraft despite aircraft thrust requirements. Previously, some compressed air flow has been bypassed in order to maintain compressor stability, but unfortunately such bypass systems within turbine engines can have a thrust recovery regime such that there is excess thrust in comparison with that actually necessary. In accordance with the present invention, a proportion of the compressed air flow is bled directly through a bleed path to an exhaust nozzleof an engine such that the compressor core can continue to provide work to drive an ancillary machine whilst engine thrust is limited to that actually required, achieving a significant saving in terms of fuel consumption and wear and tear upon brakes, etc under low power operation.