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:
Dec. 29, 1992
Filed:
Nov. 09, 1990
William R Hines, Montgomery, OH (US);
General Electric Company, Cincinnati, OH (US);
Abstract
A method of operating a dual rotor gas turbine engine includes bypassing a predetermined portion of compressed airflow from a high pressure compressor to downstream of a high pressure turbine first stage nozzle, and increasing core speed of the engine to a value greater than a reference value for improving hot day lapse rate curve and output shaft horsepower. The method steps are performed at least at values of ambient air temperature greater than a first value thereof associated with a reference maximum value of output shaft horsepower, and without increasing high pressure compressor discharge air temperature beyond a maximum value thereof associated with the reference maximum value of the output shaft horsepower. The dual rotor, gas turbine engine includes a preexisting design, aircraft derivative core engine including a high pressure compressor and a high pressure turbine first stage nozzle. A portion of compressed airflow from the high pressure compressor is bypassed to a point downstream of the high pressure turbine first stage nozzle, and core speed is increased for increasing output shaft horsepower of a low pressure turbine without increasing high pressure compressor discharge air temperature beyond a maximum value thereof.