AIR INJECTION INTO GAS TURBINE ENGINE COMPRESSOR PATH Russian patent published in 2013 - IPC F04D29/68 F04D27/00 F02C9/18 

FIELD: engines and pumps.

SUBSTANCE: compressor of gas turbine engine contains annular housing (14) and annular row of straightener blades with adjustable installation angle. Each blade has an airfoil (16), one end of which is connected via the plate (17) to round contour with cylindrical radial trunnion (18) directed to rotation in corresponding housing (14) hole. Each blade at rotation moves around the axis defined by the blade trunnion between the first and the second position. Each of the plates of, at least, some blades has the channel (40) for air supply into the passage (46) that is formed in housing. One end of the passage opens to compressor path for air injection to this path at blade inlet. Supply channel formed in the plate has the end designed for connection to corresponding housing passage, when the blade is in its first position and closed by housing, when the blade is located in its second position so that air injection flow rate depends upon blade inclination angle.

EFFECT: improvement of engine characteristics at low or intermediate operation modes by means of joint control of injected air flow rate and blade inclination angle.

14 cl, 9 dwg