US 12,264,622 B2
Gas turbine air bleed arrangement with an inlet
Carlos Arroyo, Trollhättan (SE); Hans Mårtensson, Trollhättan (SE); and Mattias Billson, Trollhättan (SE)
Assigned to GKN AEROSPACE SWEDEN AB, Trollhättan (SE)
Appl. No. 18/008,469
Filed by GKN Aerospace Sweden AB, Trollhättan (SE)
PCT Filed Jun. 25, 2021, PCT No. PCT/EP2021/067481
§ 371(c)(1), (2) Date Dec. 6, 2022,
PCT Pub. No. WO2021/260173, PCT Pub. Date Dec. 30, 2021.
Claims priority of application No. 2009749 (GB), filed on Jun. 26, 2020.
Prior Publication US 2023/0203987 A1, Jun. 29, 2023
Int. Cl. F02C 6/08 (2006.01); F02C 7/24 (2006.01)
CPC F02C 6/08 (2013.01) [F02C 7/24 (2013.01); F05D 2240/127 (2013.01); F05D 2250/184 (2013.01); F05D 2250/51 (2013.01); F05D 2260/606 (2013.01); F05D 2260/963 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A gas turbine engine component, comprising:
a duct including at least one generally radially extending bleed passage in fluid communication with an outlet for releasing air from the duct,
wherein the bleed passage has an inlet in fluid communication with the duct, the inlet being defined between an upstream leading edge and downstream trailing edge arranged facing each other along a direction of flow of air through the duct,
wherein the upstream leading edge of the inlet has a non-uniform profile extending into the inlet and the bleed passage along the direction of flow of air through the duct, or the downstream trailing edge of the inlet has a non-uniform profile extending into the inlet and the bleed passage along the direction of flow of air through the duct, and
wherein the non-uniform profile of the upstream leading edge of the inlet or the downstream trailing edge of the inlet is in the form of an undulating surface having portions which extend to a greater distance along the direction of airflow through the duct than other portions.