US 12,276,229 B2
Method of operating a turbine engine having a bleed system
Brandon W. Miller, Middletown, OH (US); Geoffrey Whitener, Cincinnati, OH (US); Jeffrey D. Clements, Mason, OH (US); Patrick Marrinan, Cincinnati, OH (US); and Andrew J. Hank, Maineville, OH (US)
Assigned to GENERAL ELECTRIC COMPANY, Evendale, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Sep. 8, 2023, as Appl. No. 18/463,800.
Prior Publication US 2025/0084797 A1, Mar. 13, 2025
Int. Cl. F02C 9/18 (2006.01)
CPC F02C 9/18 (2013.01) [F05D 2260/606 (2013.01); F05D 2270/3061 (2013.01)] 19 Claims
OG exemplary drawing
 
1. A method of operating a turbine engine having a high-pressure compressor including a high-pressure compressor flowpath and a plurality of stages of high-pressure compressor rotor blades and high-pressure compressor stator vanes, and a bleed system comprising a plurality of bleed flowpaths including a first bleed flowpath from one stage of the plurality of stages and a second bleed flowpath from another stage of the plurality of stages, the method comprising:
directing compressed air through the high-pressure compressor flowpath;
directing a first portion of the compressed air through the first bleed flowpath, the first portion of the compressed air having a first mass flow;
directing a second portion of the compressed air through the second bleed flowpath, the second portion of the compressed air having a second mass flow;
determining an altitude of the turbine engine; and
changing the first mass flow of the first portion of the compressed air through the first bleed flowpath as the altitude of the turbine engine increases or decreases,
wherein a mass flow ratio of the first mass flow to the second mass flow is a first value at a first altitude, a second value at a second altitude, and a third value at a third altitude, the third altitude being greater than the second altitude, and the second altitude being greater than the first altitude.