| 摘要 |
<p>According to the invention, a recuperated micro gas turbine combustor has a casing (23), liner (27), fuel injector (33) and a flame stabilization device (29). This flame stabilization device is characterized by a swirl strength and air passage geometry as such that the pressure loss over the device is less than 1,5%. The flame stabilization device and the fuel injector form together with the liner inlet/head hardware a single burner. The position of the fuel injector with respect to the flame stabilization device is optimized for limited fuel mixing with only part of the air through the flame stabilization device. The burner first stages combustion of the mixed fuel and then mixing with the remaining air. Particularly, combustion is complete and mixing occurs as such that NOx can never increase above single-digit ppm.</p> |
