A rotor for a thermal turbomachine, in particular a gas turbine, is configured to conduct a medium in its interior. In order to conduct the medium in the interior with low flow losses, it is provided that a rotor disk of the compressor has holes, in order to feed the medium from outside into the rot
A rotor for a thermal turbomachine, in particular a gas turbine, is configured to conduct a medium in its interior. In order to conduct the medium in the interior with low flow losses, it is provided that a rotor disk of the compressor has holes, in order to feed the medium from outside into the rotor interior. For improved temperature control of the rotor disk, the holes conduct the medium through the rotor disk counter to the flow direction in the compressor.
대표청구항▼
1. A turbomachine rotor, comprising: a compressor section and a turbine section, the compressor section comprising a first rotor disk,wherein the first rotor disk comprises a first disk web which runs about a rotational axis, a first hub region which adjoins the first disk web on the side which poin
1. A turbomachine rotor, comprising: a compressor section and a turbine section, the compressor section comprising a first rotor disk,wherein the first rotor disk comprises a first disk web which runs about a rotational axis, a first hub region which adjoins the first disk web on the side which points toward the rotational axis and a first central opening, a radially outwardly pointing first ring region for receiving rotor blades, and a first collar which protrudes on both sides in an axial direction between the first disk web and the first ring region, anda plurality of first holes which are distributed about a circumference of the first rotor disk and which penetrate the first disk web toward the inside, starting from the first collar and/or the first ring region, in an inclined manner with respect to a radial direction,wherein the plurality of first holes extend from a downstream side of the first ring region to an upstream side of the first disk web. 2. The turbomachine rotor as claimed in claim 1, wherein the plurality of first holes open into a first ring face of the first rotor disk, which ring face is arranged obliquely with respect to the radial direction. 3. The turbomachine rotor as claimed in claim 2, wherein, in a radially inwardly adjacent manner with respect to the first ring face, a first upstream hub region comprises a multiplicity of ribs for forwarding a flow of air which can flow through the plurality of first holes. 4. The turbomachine rotor as claimed in claim 3, the compressor section further comprising: a second rotor disk which adjoins the first rotor disk on an upstream side of the first rotor disk and which comprises a second disk web and, on a side which points toward the rotational axis, a second hub region and a second central opening and, at its radially outer end, a second ring region for receiving rotor blades, the second hub region comprising a projecting length on both sides in the axial direction, at least a projecting length immediately upstream of the first rotor disk comprising an outwardly pointing, freely ending annular auxiliary web with the formation of an annular recess. 5. The turbomachine rotor as claimed in claim 4, wherein the multiplicity of ribs and the auxiliary web are radially aligned with each other so that the auxiliary web also partly defines flow paths between the multiplicity of ribs. 6. A turbomachine rotor, comprising: a compressor section and a turbine section, the compressor section comprising a first rotor disk,wherein the first rotor disk comprises a first disk web which runs about a rotational axis, a first hub region which adjoins the first disk web on the side which points toward the rotational axis and a first central opening, a radially outwardly pointing first ring region for receiving rotor blades, and a first collar which protrudes on both sides in an axial direction between the first disk web and the first ring region, anda plurality of first holes which are distributed about a circumference of the first rotor disk and which penetrate the first disk web toward the inside, starting from the first collar and/or the first ring region, in an inclined manner with respect to a radial direction,wherein, in a radially inwardly adjacent manner, a first upstream hub region comprises a multiplicity of ribs for forwarding a flow of air which can flow through the plurality of first holes. 7. A turbomachine rotor, comprising: a compressor section and a turbine section, the compressor section comprising a first rotor disk and a second rotor disk; wherein the first rotor disk comprises: a first disk web between a first hub and a first ring region configured to receive rotor blades; and a plurality of holes, each hole of the plurality of holes comprising a first opening arranged in a downstream side of the first ring region, a second opening arranged at an upstream ring face of the first rotor disk web which is arranged radially inward of the first opening and which is arranged obliquely with respect to a radial direction of the first rotor disk; wherein the first hub comprises a first central opening therethrough and a multiplicity of radially oriented ribs configured to party define radially oriented flow paths therebetween, the flow paths providing fluid communication between the plurality of holes and the first central opening; wherein the second rotor disk is disposed upstream of the first rotor disk and comprises a second disk web comprising a second hub region and a second ring region configured to receive the rotor blades; wherein the second hub region comprises a projecting length on both sides of the second disk web in an axial direction of the turbomachine rotor, one of the projecting lengths comprising an outwardly pointing freely ending annular auxiliary web; and wherein the turbomachine rotor is configured such that the multiplicity of radially oriented ribs and the auxiliary web are radially aligned so that the auxiliary web also partly defines the flow paths between the multiplicity of radially oriented ribs.
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이 특허에 인용된 특허 (5)
Avignon, Philippe; Brunet, Antoine Robert Alain; Pasquis, Patrick Claude, Axial compressor disk for a turbomachine with centripetal air bleed.
Stratford Brian S. (Derby GB2) Hadaway Edward S. (Derby GB2) Chew John (Derby GB2) Hartland Howard G. (Derby GB2), Compressor and air bleed arrangement.
Stenneler Jacques M. P. (Le Chatelet En Brie FRX) Naudet Jacky (Evry FRX), Turbine plant compressor disc with centripetal accelerator for the induction of turbine cooling air.
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