METHOD AND APPARATUS FOR MEASURING COMPRESSOR BLEED FLOW

A gas turbine engine includes a compressor, an annular casing (44) surrounding the compressor, and a bleed flow adapter (56) mounted to an exterior side of the annular casing (44). The annular casing (44) includes an interior side that surrounds a compressor bleed cavity (50) located downstream of at least a portion of the compressor. The bleed flow adapter (56) is in fluid communication with the compressor bleed cavity (50) and includes an inlet end (62), an outlet end (64), and an inner diameter surface (66) extending between the inlet end (62) and the outlet end (64). The inner diameter surface (66) defines a bleed passage (68). The bleed flow adapter (56) further includes a fluid port (76) formed through the inner diameter surface (66). The gas turbine engine further includes a bleed flow measurement system (80) including a first pressure sensor (84) in fluid communication with the bleed passage (68) of the bleed flow adapter (56) via the fluid port (76).