Casing for a gas turbine engine

摘要

A casing for a can annular gas turbine engine, including: a compressed air section (40) spanning between a last row of compressor blades (26) and a first row of turbine blades (28), the compressed air section (40) having a plurality of openings (50) there through, wherein a single combustor/advanced duct assembly (64) extends through each opening (50); and one top hat (68) associated with each opening (50) configured to enclose the associated combustor/advanced duct assembly (64) and seal the opening (50). A volume enclosed by the compressed air section (40) is not greater than a volume of a frustum (54) defined at an upstream end (56) by an inner diameter of the casing at the last row of compressor blades (26) and at a downstream end (60) by an inner diameter of the casing at the first row of turbine blades (28).

主权项

1. A casing for a can annular gas turbine engine, comprising:
a compressed air section comprising an upstream portion configured to secure to a compressor casing at a last row of compressor blades and a downstream portion configured to secure to a turbine casing at a first row of turbine blades such that the compressed air section, the compressor casing, and the turbine casing share a common longitudinal axis, the compressed air section further comprising a plurality of openings therethrough and arranged in an annular array having an origin located on the common longitudinal axis, wherein a respective combustor/advanced duct assembly extends through a respective opening of the plurality of openings; and one top hat from a plurality of top hats for each opening of the plurality of openings, each one of the plurality of top hats configured to attach to the compressed air section, to enclose the respective combustor/advanced duct assembly, and to seal the respective opening of the plurality of openings, wherein a volume enclosed by the compressed air section is not greater than a volume of a frustum that is defined at an upstream end by an inner diameter of the compressor casing at the last row of compressor blades and at a downstream end by an inner diameter of the turbine casing at the first row of turbine blades.