US 12,071,903 B2
Assisted engine start bleed system
Daniel Bernard Kupratis, Wallingford, CT (US); Martin Richard Amari, Glastonbury, CT (US); and Geoffrey T. Blackwell, Vernon, CT (US)
Assigned to RTX Corporation, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on May 1, 2020, as Appl. No. 16/864,881.
Claims priority of provisional application 62/842,024, filed on May 2, 2019.
Prior Publication US 2021/0199056 A1, Jul. 1, 2021
Int. Cl. F02C 9/18 (2006.01); F02C 7/26 (2006.01)
CPC F02C 9/18 (2013.01) [F02C 7/26 (2013.01); F05D 2240/127 (2013.01); F05D 2260/606 (2013.01); F05D 2260/85 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A system for bleeding air from a core flow path of a gas turbine engine, comprising: a bleed valve in a bleed air duct configured to receive bleed air from a first entrance point to the core flow path into the bleed air duct; a pressurized air valve in a pressurized air duct configured to receive pressurized air from a second entrance point to the core flow path, the pressurized air at a pressure greater than that received into the first entrance point, wherein the bleed air duct is of a larger diameter than the pressurized air duct; an eductor outlet from the pressurized air duct located in the bleed air duct, wherein the bleed air duct extends along a linear bleed air flow path, and wherein at least a portion of the pressurized air duct and the eductor are positioned within the bleed air duct along the linear bleed air flow path; and a control system operable to control operation of the bleed valve and the pressurized air valve, and a pressure throttling valve in the bleed air duct downstream of the eductor valve.