| 摘要 |
<p>The invention is directed to a turbine arrangement (1) or a gas turbine engine comprising a plurality of turbine arrangements (1), the turbine arrangement (1) comprising a first platform (2), a second platform (3), a plurality of aerofoils (4A, 4B), and an impingement plate (7). Each of the plurality of aerofoils (4A, 4B) is extending between the first platform (2) and the second platform (3), the first and second platform (3) forming a section of a main fluid path. The second platform (3) has a surface opposite to the main fluid path with a plurality of recesses (5A, 5B), the recesses (5A, 5B) surrounded by a raised edge (6), the edge (6) providing a support for the mountable impingement plate (7). According to the invention the edge (6) is formed as a first closed loop surrounding a first recess (5A) of the plurality of recesses (5A, 5B) and further surrounding a first aperture (8A) of a first aerofoil (4A) of the plurality of aerofoils (4A, 4B) and as a second closed loop surrounding a second recess (5B) of the plurality of recesses (5A, 5B) and further surrounding a second aperture (8B) of a second aerofoil (4B) of the plurality of aerofoils (4A, 4B), such that a portion of the edge (6) defines a continuous barrier (9) between the first recess (5A) and the second recess (5B) for blocking cooling fluid, and such the barrier (9) forms a mating surface for a central area (11) of the impingement plate (7).</p> |
