US 12,320,304 B2
Gas turbine engine including a compressor bleed air system
Meredith Wulff, North Reading, MA (US); Jonathan Atef Tawfik, Arlington, MA (US); and Jesse Ollove, Tewksbury, MA (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Aug. 18, 2023, as Appl. No. 18/452,205.
Prior Publication US 2025/0059920 A1, Feb. 20, 2025
Int. Cl. F02C 9/18 (2006.01); F04D 27/00 (2006.01); F04D 29/52 (2006.01)
CPC F02C 9/18 (2013.01) [F04D 27/009 (2013.01); F04D 29/522 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a compressor; and
a compressor bleed air system including:
a compressor shroud defining a compressor airflow passage therewithin;
a compressor bleed air plenum;
a plurality of compressor stator vanes connected with the compressor shroud and extending into the compressor airflow passage, the plurality of compressor stator vanes being arranged circumferentially spaced apart from each other within a stator vane stage of the compressor; and
a plurality of compressor bleed air passages arranged through the compressor shroud within the stator vane stage and providing fluid communication between the compressor airflow passage and the compressor bleed air plenum, each of the plurality of compressor bleed air passages including an inlet at the compressor airflow passage and an outlet at the compressor bleed air plenum,
wherein respective inlets of respective ones of the plurality of compressor bleed air passages are arranged circumferentially spaced apart from one another about a centerline axis of the compressor shroud, a first compressor bleed air passage of the plurality of compressor bleed air passages and a second compressor bleed air passage of the plurality of compressor bleed air passages are arranged circumferentially adjacent to one another and an inlet of the first compressor bleed air passage and an inlet of the second compressor bleed air passage are circumferentially spaced apart from one another by a first angular spacing, and respective inlets of at least a portion of a remainder of the plurality of compressor bleed air passages circumferentially sequentially arranged adjacent to each other are circumferentially spaced apart from one another by a second angular spacing, the second angular spacing being less than the first angular spacing,
wherein each one of the plurality of compressor stator vanes includes a leading edge and a trailing edge extending along an axial direction along the centerline axis, and a base connecting the compressor stator vane to the compressor shroud, the stator vane stage being defined axially between the leading edge and the trailing edge, and
wherein each one of the plurality of compressor bleed air passages is arranged circumferentially within the stator vane stage between a respective pair of compressor stator vanes among the plurality of compressor stator vanes.