Assembly for controlling the flow of cooling air in an engine turbine

Claim 2

In an engine turbine comprising turbine rotor discs having sockets in the outer peripheries thereof, turbine rotor blades mounted on said discs with root portions of said blades in said sockets, cooling passages at the bottom of said sockets for the flow of cooling air therethrough, labyrinth carriers separating said discs, and an assembly for controlling the flow of cooling air through said passages comprising annular closure means at the upstream and downstream ends of said labyrinth carriers adapted selectively to block and unblock said cooling passages in response to differential radial expansion of said discs and said labyrinth carriers, blocking of said passages being determined by the positions of said closure means and of said passages, which positions are in turn determined by the dimensions and thermal expansion coefficients of said discs and said labyrinth carriers.

Claim 3

A control assembly in an engine turbine according to claim 1, wherein each of said labyrinth carriers has a pin-like profile and comprises a cylindrical outer part carrying labyrinth members, a frusto-conical supporting wall extending inwardly from one end of said outer part, and a radially inwardly extending annular portion at the inner end of said supporting wall for attachment to said turbine rotor discs, and said annular closure means at at least one end of each of said labyrinth carriers comprises a peripheral support collar disposed on said outer part at the end thereof and adapted to bear at least partly against part of said blade roots of the adjacent disc to prevent axial displacement of said roots and to block or partly block said cooling passage of said adjacent disc.

Claim 4

A control assembly in an engine turbine according to claim 2, wherein said annular closure means at said downstream end of each of said labyrinth carriers comprises a peripheral collar disposed on said outer part at the downstream end thereof, and an annular shoulder provided on the downstream face of said collar and adapted to bear against part of the adjacent disc and said blade roots thereof to block or partly block said cooling passage of said adjacent disc.

Claim 5

A control assembly in a turbine according to claim 3, wherein said supporting wall of each of said labyrinth carriers defines a space with said disc upstream thereof, and defines a chamber with said disc downstream thereof and with said outer part, said cooling passage of said upstream disc opening into one end of said space, said supporting wall including openings communicating the other end of said space with said chamber, and said chamber communicating with the cooling passage of said downstream disc.

Claim 6

A control assembly in a turbine according to claim 4, wherein said assembly is associated with the first three stages of a low pressure turbine of said engine, and said cooling air is taken from the compressor of said engine, said assembly being operative such that, when said annular closure means do not fully block said cooling passages, said cooling air enters the cooling passage of the first disc, exits through the opening defined between the outlet of said passage and said peripheral support collar of the first labyrinth carrier, undergoes expansion in said space and said chamber formed between said first and second discs, enters the opening defined between said annular shoulder of said first labyrinth carrier and the inlet of said cooling passage of said second disc, exits through the opening defined between the outlet of said second disc cooling passage and said peripheral support collar of the second labyrinth carrier, undergoes expansion in said space and said chamber formed between said second and third discs, enters the opening defined between said annular shoulder of said second labyrinth carrier and the inlet of said cooling passage of said third disc, and escapes freely from the outlet of said third disc cooling passage.