Device for regulating turbine blade tip clearance
AssigneeSociete Nationale d'Etude et de Construction de Moteurs d'Aviation
InventorsClaude Christian Hallinger, Robert Kervistin
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Abstract
A device for automatically regulating the clearance between the tips of the otor blades of a turbine, particularly of a gas turbine, and the adjacent wall of a turbine stator, comprising means for directing a gaseous flow against the said wall to regulate its temperature. This gaseous flow is obtained from a proportioner including at least two inlet passages connected to sources of gas at different temperatures and controlled by the thermal expansion of an obturator responsive to the temperature of fluid passing through the turbine, so as to reduce the temperature of the said gaseous flow as the obturator expands, in order to cool the stator in stable conditions and to heat it in transitory conditions.
Claims11
A device for regulating the clearance between the tips of the rotor blades of a turbine supplied with a hot fluid and the turbine stator facing the said blades, comprising a first source of gas suitable for supplying gas at a first temperature, a second source of gas suitable for supplying gas at a second temperature lower than the first temperature, a proportioner having a first and a second inlet passage and an outlet passage, means connecting the first inlet passage to the first source of gas and the second inlet passage to the second source of gas, an obturator capable of being expanded thermally to reduce the cross-section of the first inlet passage and to increase the cross-section of the second inlet passage, means whereby a portion of the obturator is contacted by said hot fluid, and means connecting the outlet passage to the said wall to direct thereupon a flow of gas issuing from the said outlet passage.
Dependencies are inferred from the claim text.