Patent ID: 6726446
Filing Date: 2004-04-27
Classification: F01D,F05B,F05D

Abstract:
Support spacer sector (14) for the stator ring (12) of a high pressure turbine in a turbomachine with compensation for the clearances of the spacer sector assembly (14) and functional clearances (J) between the ring sectors (12) and the ends of the blades (3) of the rotor, this sector comprising:an upstream radial wall (14M) with an external upstream hook (16M) that will be axially engaged in an corresponding upstream notch (17M) on the high pressure casing (1) of the turbomachine; an internal upstream hook (18M) that will be engaged in a corresponding upstream notch (19M) in a ring sector (12); a downstream radial wall (14V) with an external downstream hook (16V) that will be axially engaged in a corresponding downstream notch (17V) on the high pressure casing (1) of the turbomachine; an internal downstream hook (18V) that will be fixed to the corresponding ring sector (12), and a longitudinal tab (20) fixed on the outside of the wall, with an outside thrust surface (22) at its upstream end (21) that projects towards the outside, so that it is in contact on the inside (1I) of the turbomachine high pressure turbine casing (1) and exerts pressure on it when the support spacer sector (14) is in place, characterized in that the tab (20) is fixed on the upstream side of the upstream wall (14M), the radial thrust surface (22) of the end (21) of the upstream tab (20) is not continuous but is separated by recesses (23) such that gases can pass through.