Abstract: A swirler for mixing fuel with air in a combustion engine includes a central axis, a swirler base with an upper surface, a central portion, a number of main swirler elements and a number of obstruction elements. The main swirler elements and the obstruction elements are located at the upper surface of the swirler base and are arranged around the central portion. The main swirler elements form a number of swirler slots configured for directing a fluid towards the central portion. Each swirler slot has a slot inlet and a slot outlet, wherein the slot outlet is located at a smaller radial distance from the central axis than the swirler inlet. Each obstruction element is located at a slot inlet and configured for forming a plurality of flow channels into the swirler slot.

Abstract: A bearing device supports a shaft of a gas turbine engine. A first support disk is mounted to the bearing housing element. First tilting pads are tiltably arranged one after another along a circumferential direction at the first support disk. A second support disk is mounted to the bearing housing element spaced apart from the first support disk along an axial direction. Second tilting pads are tiltably arranged one after another along the circumferential direction at the second support disk. A first number of the first tilting pads is greater than the half of a second number of the second tilting pads but smaller than the second number of the second tilting pads.

Abstract: A swirler for mixing fuel with air in a combustion engine includes a central axis, a swirler base with an upper surface, a central portion, a number of main swirler elements and a number of obstruction elements. The main swirler elements and the obstruction elements are located at the upper surface of the swirler base and are arranged around the central portion. The main swirler elements form a number of swirler slots configured for directing a fluid towards the central portion. Each swirler slot has a slot inlet and a slot outlet, wherein the slot outlet is located at a smaller radial distance from the central axis than the swirler inlet. Each obstruction element is located at a slot inlet and configured for forming a plurality of flow channels into the swirler slot.

Abstract: A combustor for a gas turbine having: a pre-combustion chamber, a swirler, a pilot burner upstream the pre-combustion chamber which has a pilot burner surface separating the pilot burner from the pre-combustion chamber. The pilot burner further includes at least a pilot fuel injector, wherein the combustor includes a lip extending from the pilot burner surface in the pre-combustion chamber, the lip including an internal surface oriented towards the pilot fuel injector, the internal surface being inclined of an inclination angle of between 0 degrees and 90 degrees with respect to the center axis of the pre-combustion chamber, and the lip has at least a feed passage for connecting the internal surface with the flow of oxidant gas coming from the swirler.

Abstract: A bearing device supports a shaft of a gas turbine engine. A first support disk is mounted to the bearing housing element. First tilting pads are tiltably arranged one after another along a circumferential direction at the first support disk. A second support disk is mounted to the bearing housing element spaced apart from the first support disk along an axial direction. Second tilting pads are tiltably arranged one after another along the circumferential direction at the second support disk. A first number of the first tilting pads is greater than the half of a second number of the second tilting pads but smaller than the second number of the second tilting pads.