Patent ID: 7658061
Filing Date: 2010-02-09
Classification: F02C,F02K,F05D,Y02T

Abstract:
1. A gas turbine engine, comprising: an outer casing; an inner casing received in the outer casing so as to define a bypass duct having an annular cross section in cooperation with the outer casing; an outer liner received in the inner casing; an inner liner received in the outer liner so as to define an intake passage in cooperation with the outer liner; a first compressor provided in a downstream end of the intake passage; a combustor connected to an outlet end of the first compressor; a turbine provided adjacent to an outlet end of the combustor; a rotary shaft rotatably received in the inner liner and having a front fan attached to a front end thereof adjacent to both an inlet end of the bypass duct and an inlet portion of the intake passage, the rotary shaft further carrying a impeller wheel of the first compressor and a turbine wheel of the turbine at appropriate parts thereof; and a foreign matter removal passage communicating with the intake passage via a plurality of foreign matter introduction openings formed in the outer liner and with the bypass duct via a plurality of foreign matter ejection openings formed in the inner casing, wherein the foreign matter removal passage comprises an annular space surrounding the rotary shaft.