Sealing device for turbine blades of a turbojet engine

Details Sealing device for turbine blades of a turbojet engine Sealing device for turbine blades of a turbojet engine

1984-01-30

1985-07-09

Garrett, Robert E.

Power plants

Combustion products used as motive fluid

415116, 415138, 415170R, 60 3975, F01D 1108, F02C 618

Patent

active

045273855

ABSTRACT:
A sealing device is disclosed for maintaining a small positive clearance between the sealing sectors and the turbine blade tips of a turbojet engine. The sealing segments are connected to an internal ring structure and an external ring structure located within the casing of the jet engine. The two ring structures serve to expand and contract the diameter of the ring formed by the sealing segments in conjunction with the expansion and contraction of the turbine blades for stabilized and transient engine operating modes. The device utilizes ventilating air taken from a stage of the jet engine compressor to cause the radial expansion or contraction of the internal and external rings in direct conjunction with the conditions under which the engine is operating.

REFERENCES:
patent: 3807891 (1974-04-01), McDow et al.
patent: 3966354 (1976-06-01), Patterson
patent: 4019320 (1977-04-01), Redinger, Jr. et al.
patent: 4127357 (1978-11-01), Patterson
patent: 4363599 (1982-12-01), Cline et al.

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