| 摘要 |
<p>The invention concerns a gas turbine engine (1, 100, 500, 600, 700) comprising in serial flow relationship: a first compressor (22, 122, 722) provided with at least one row of compressor blades (27, 127a, 127b, 127c, 127d, 727) distributed circumferentially around the first compressor (22, 122, 722); a combustion chamber (23); and a first turbine (24, 124) provided with at least one row of turbine blades (28, 128) distributed circumferentially around the first turbine (24, 124), wherein the first compressor (22, 122, 722) and the first turbine (24, 124) are rotationally rigidly connected by a first shaft (29, 129). The invention is characterized in that the first turbine (24, 124) is adapted to influence a gas flow rate through the gas turbine engine (1, 100, 500, 600, 700) depending on a rotational speed of the first turbine (24, 124), wherein the gas turbine engine (1, 100, 500, 600, 700) further comprises means (33, 133, 733) for controlling the rotational speed of the first turbine (24, 124). The invention also concerns a method for controlling a gas flow rate in an axial flow gas turbine engine.</p> |
