초록 ▼

A turbo compressor in an axial type of construction is disclosed. The turbo compressor has a bladed stator and a bladed rotor, and has a longitudinally split compressor casing and a guide blade ring with adjustable guide blades. The guide blades are pivotably mounted about radial axes radially withi

A turbo compressor in an axial type of construction is disclosed. The turbo compressor has a bladed stator and a bladed rotor, and has a longitudinally split compressor casing and a guide blade ring with adjustable guide blades. The guide blades are pivotably mounted about radial axes radially within their aerofoil on an inner ring belonging to the stator. The inner ring is split, i.e., segmented, at at least two points of its circumference. Furthermore, the inner ring has for each guide blade at least one bearing bush which can be inserted radially into an opening from inside.

대표청구항 ▼

1. A turbo compressor in an axial type of construction for a gas turbine, comprising a bladed stator and a bladed rotor, wherein the bladed stator includes a compressor casing that is longitudinally split on diametrically opposed sides and at least one guide blade ring with adjustable guide blades,

1. A turbo compressor in an axial type of construction for a gas turbine, comprising a bladed stator and a bladed rotor, wherein the bladed stator includes a compressor casing that is longitudinally split on diametrically opposed sides and at least one guide blade ring with adjustable guide blades, wherein the adjustable guide blades are pivotably mounted about a respective radial axis on an inner ring of the bladed stator, and wherein the inner ring includes at least two segments around its circumference and includes for each adjustable guide blade a bearing bush which is insertable radially into an opening defined by the inner ring from a radial inside direction with respect to the inner ring and further comprising a sealing support with a rub coating or run-in coating detachably fastened on the inner ring, wherein the sealing support secures the bearing bush from falling out of the opening. 2. The turbo compressor according to claim 1, wherein each segment of the inner ring is deformable by bending from a first radius in an unstressed state to a second defined smaller radius. 3. The turbo compressor according to claim 1, wherein the inner ring is bisected into two segments extending respectively over an angle of approx. 180°. 4. The turbo compressor according to claim 1, wherein the sealing support includes at least two segments around its circumference and is held on the segments of the inner ring by radial form closure. 5. The turbo compressor according to claim 4, wherein the sealing support is bisected into two segments and wherein each of the two segments of the sealing support is comprised of a radially form-fit sheet metal profile that is complementary to the inner ring and includes a honeycomb structure as the rub coating or run-in coating. 6. The turbo compressor according to claim 1, wherein the compressor casing, for each adjustable guide blade, has at least one bearing bush that is insertable radially from a radial outside direction with respect to the casing into an opening defined by the casing. 7. The turbo compressor according to claim 6, wherein the openings for the bearing bushes in the inner ring and/or the openings for the bearing bushes in the casing are bore holes, counter-bores and/or cut-outs. 8. The turbo compressor according to claim 1, wherein each adjustable guide blade has a plate-like disk on a radially inner end and on a radially outer end of an aerofoil of the guide blade, and wherein at least the plate-like disk on the radially inner end has a conical or spherical taper towards the bearing bush. 9. The turbo compressor according to claim 1, wherein each of the segments of the inner ring is a monolithic structure. 10. The turbo compressor according to claim 1, wherein each of the segments of the inner ring is a monolithic structure along an entire axial length of the inner ring. 11. The turbo compressor according to claim 10, wherein each of the segments of the inner ring extends 180° or less around a circumference of the inner ring. 12. The turbo compressor according to claim 10, wherein the openings are defined by the monolithic structure. 13. The turbo compressor according to claim 12, wherein the openings are included on a radially inner side of the segments of the inner ring. 14. The turbo compressor according to claim 1, wherein the sealing support directly engages with the bearing bush.