초록 ▼

In a gas turbine engine bladed disk (36) positioned between rotor disk (14) and combustor (16). Bladed disk (36) is mounted for rotation together with rotor disk (14) and has blades (38) projecting toward inlet portion (20) of combustor (16). The bladed disk has openings (40) between blades (38) for

In a gas turbine engine bladed disk (36) positioned between rotor disk (14) and combustor (16). Bladed disk (36) is mounted for rotation together with rotor disk (14) and has blades (38) projecting toward inlet portion (20) of combustor (16). The bladed disk has openings (40) between blades (38) for establishing communication between source of compressed fluid (12) and turbine blades (15). Seals (46, 48) are provided between bladed disk (36) and casing (10).

대표청구항 ▼

[ What is claimed is:] [1.]1. A gas turbine engine, said gas turbine engine comprising:a source of compressed fluid flow;a fuel source;a combustion air source;a casing;a combustor in said casing, said combustor having an annular inner wall and an annular guide wall extending in a spaced relation to

[ What is claimed is:] [1.]1. A gas turbine engine, said gas turbine engine comprising:a source of compressed fluid flow;a fuel source;a combustion air source;a casing;a combustor in said casing, said combustor having an annular inner wall and an annular guide wall extending in a spaced relation to said annular inner wall and defining therewith an inlet portion, said combustor communicating with said fuel source and with said combustion air source to prepare a heated fluid;a turbine rotor disk with turbine blades, said turbine blades positioned immediately downstream of said combustor for receiving said heated fluid from said combustor;a means for imparting a spin to said heated fluid within said combustor, said means comprising a bladed disk positioned between said rotor disk and combustor, said bladed disk being mounted for rotation together with said rotor disk, having blades projecting toward said inlet portion of said combustor and openings between said blades, said openings establishing communication between said source of compressed fluid and said turbine blades; anda sealing means between said bladed disk and said casing.