초록 ▼

An air-guiding system between a compressor and a turbine of a gas turbine engine includes an air chamber (5) being delimited by the inner casing of the combustion chamber (4) and first and second seals (7, 8) towards the rotating compressor shaft cone (12). An axial thrust compensation chamber (6) i

An air-guiding system between a compressor and a turbine of a gas turbine engine includes an air chamber (5) being delimited by the inner casing of the combustion chamber (4) and first and second seals (7, 8) towards the rotating compressor shaft cone (12). An axial thrust compensation chamber (6) is adjoined to said second seal (8) and respectively loaded with the turbine cooling air (B', C) branched-off from the compressor air. Due to the higher pressure in said axial thrust compensation chamber with respect to said air chamber, the high axial forces are compensated. The air flowing back into said air chamber through said second seal (8) is guided and separated from components (10) and flowing-off air masses by a flow-guiding means (16) in said air chamber. This results in a high rinsing effect, a reduced vortex formation and finally, a reduced thermal stress.

대표청구항 ▼

The invention claimed is: 1. An air-guiding system between a compressor and a turbine of a gas turbine engine operated with a high pressure ratio, comprising: an air chamber adjoined to the compressor and passed through by a first turbine cooling air, said air chamber being delimited radially by an

The invention claimed is: 1. An air-guiding system between a compressor and a turbine of a gas turbine engine operated with a high pressure ratio, comprising: an air chamber adjoined to the compressor and passed through by a first turbine cooling air, said air chamber being delimited radially by an inner casing of a combustion chamber and a compressor shaft cone and axially by a first seal arranged upstream and a second seal arranged downstream, air exhaust ports spaced from a gap formed between the second seal and said compressor shaft cone, an axial thrust compensation chamber adjoined to said second seal and being loaded with a second turbine cooling air having a higher pressure, and flow-guiding means positioned in a rear portion of the air chamber, extending substantially axially and located between the seal gap of said second seal and said air exhaust ports. 2. An air-guiding system according to claim 1, wherein said flow-guiding means is a circumferential air-guiding ring positioned at the rear portion of said air chamber, which guides the second turbine cooling air flowing into the air chamber through the seal gap of said second seal from said axial thrust compensation chamber and along said compressor shaft cone and separates it from the first turbine cooling air flowing to said air exhaust ports and from a flange connection at said inner casing of the combustion chamber. 3. An air-guiding system according to claim 2, wherein said air-guiding ring is held by fixing flange at said flange connection, and that the air flow to said air exhaust ports takes place through air-guiding ports. 4. An air-guiding system according to claim 3, wherein said air-guiding ports are air passage ports provided in said fixing flange and being elongated in the peripheral direction. 5. An air-guiding system according to claim 3, wherein said air-guiding ports are formed by guide means in the form of at least one of profiled deflection vanes, simple deflection plates and through-holes inclined with regard to a machine axis, said guide means being provided between said fixing flange and said air-guiding ring and reducing flow losses. 6. An air-guiding system according to claim 3, wherein said air-guiding ports are formed by air passage pockets provided at said air-guiding ring. 7. An air-guiding system according to claim 3, wherein said air-guiding ports are formed by a circumferential annular gap provided at said air-guiding ring. 8. An air-guiding system according to claim 2, and further comprising a covering ring attached to said air-guiding ring, which shields said flange connection and said flange against said first turbine cooling air and guides the latter to said air-guiding ports. 9. An air-guiding system according to claim 2, and further comprising a covering ring connected to the inner casing and positioned upstream of said air-guiding ring, which is arranged spaced from said inner casing of the combustion chamber and covers the latter, and reduces the air chamber volume and guides said first turbine cooling air to said air-guiding ports.