Device and method for influencing the temperatures in inner ring segments of a gas turbine
AssigneeMTU Aero Engines AG
InventorChristoph Lauer
Life of this patent
Estimating the term…
Abstract
A device for influencing the temperatures in inner ring segments of a gas turbine is provided, which includes in the circumferential direction of the gas turbine, at least one outer shell assembly having a plurality of outer ring segments and at least one inner shell assembly having a plurality of inner ring segments. The inner ring segments are equal to or greater in number than the outer ring segments. An outer ring segment gap is between each two adjacent outer ring segments. An inner ring segment gap is between each two adjacent inner ring segments. An outer ring segment gap, or at least a radial cooling air passage, is located opposite each inner ring segment gap in the radial direction of the gas turbine.
Claims22
A device for influencing the temperatures in inner ring segments of a gas turbine, comprising, in a circumferential direction of the gas turbine:
- at least one outer shell assembly having a plurality of outer ring segments;
- at least one inner shell assembly having a plurality of inner ring segments, the plurality of inner ring segments being equal to or greater in number than the plurality of outer ring segments;
- wherein an outer ring segment gap is provided between each two adjacent outer ring segments, and an inner ring segment gap is provided between each two adjacent inner ring segments;
- and
- wherein, located opposite each inner ring segment gap, in a radial direction of the gas turbine, is either one of the outer ring segment gaps or a radial cooling air passage and each inner ring segment gap has a first ship lap associated therewith, each outer ring segment gap had a second ship lap associated therewith, and each cooling air passage has a pseudo ship lap associated therewith, to deflect subflows into the same circumferential direction.
A device for influencing the temperatures in inner ring segments of a gas turbine, comprising, in a circumferential direction of the gas turbine:
- at least one outer shell assembly having a plurality of outer ring segments;
- at least one inner shell assembly having a plurality of inner ring segments, the plurality of inner ring segments being equal to or greater in number than the plurality of outer ring segments;
- a mixing space between the outer ring segments and the inner ring segments in the same circumferential direction of the gas turbine providing mixing of at least two first subflows of hot gas and at least two second subflows of cooling air in the circumferential direction of the gas turbine
- wherein an outer ring segment gap is provided between each two adjacent outer ring segments, at least one of the second subflows flowing through the outer ring segment gap in an inward radial direction;
- and an inner ring segment gap is provided between each two adjacent inner ring segments, at least one of the first subflows flowing through the inner ring segment gap in an outward radial direction;
- and
- wherein, located opposite each inner ring segment gap, in a radial direction of the gas turbine, is either one of the outer ring segment gaps or a radial cooling air passage so that at every circumferential position where the hot gas through the inner ring segment gap can enter the mixing space, the cool gas can also enter the mixing space, wherein the at least one of the second subflows flowing through the outer ring segment gap in the inward radial direction and the at least one of the first subflows flowing through the inner ring segment gap in the outward radial direction also enter the mixing space is a same circumferential direction.
Dependencies are inferred from the claim text.