To provide a gas turbine engine in which speed distribution of combustion gas passing through rotor blades and stator blades of a turbine in a peripheral direction is uniformed and performance variations among individual machines are small.
In the turbine (7) having rotor blade stages (45) comprising a plurality of the rotor blades 43 in an outer periphery, turbine rotor stages (39) forming the turbine (7) of the gas turbine engine (1) by being plurally connected in an axial direction, and stator stages (37) arranged between respective turbine rotor stages (39) and comprising a plurality of stator blades (35), the plurality of rotor blades (43) of the respective rotor stages (45) and the plurality of stator blades (35) of the respective stator stages (37) are arranged in a peripheral direction in an equal interval respectively, the ratio (r=n/m) number (n) of the rotor blades in the respective rotor stages located both the side of the stator blade stages in an axial direction to the number (m) of the stator blades in the respective stator blade stages is set within a range from 1.25 to 1.75.
SUGIMOTO TAKAO
BOHN DIETER
MORITZ NOBERT
KUSTERER KARSTEN
| JP2005220797A | 2005-08-18 | |||
| JP2002155701A | 2002-05-31 | |||
| JPS61132702A | 1986-06-20 |
| US20060257238A1 | 2006-11-16 | |||
| US4968216A | 1990-11-06 |