Rotor thrust balancing
First Claim
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1. A gas turbine construction in which the air thrust pressures on the rotor are balanced including:
- a compressor disk having a row of blades thereon,a turbine disk having a row of blades thereon,a shaft connecting said disks and having a conical portion adjacent to the compressor disk and forming, with said disks, the rotor,a first seal carried by said conical portion,a fixed seal cooperating with said first seal,a second seal carried by the turbine disk,a fixed second seal cooperating with said second seal,a bearing for the shaft between the disks,a housing surrounding said bearing,a structure surrounding said housing and defining a compartment extending between the compressor and turbine disks and having as a part of the boundry thereof the conical portion of the shaft radially inward of the first seal and, as another part, the portion of the turbine disk radially inward of the second seal, andmeans for pressurizing the compartment wherein an inner wall of combustion chamber, a support extending from said inner wall to the housing to maintain it in relation to the inner wall and holes in said support to balance the pressure on opposite sides thereof, wherein the first and second seal are at substantially the same radius with respect to the rotor thereby to expose substantially the same area to the pressure in said compartment.
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Accused Products
Abstract
A turbine construction in which the axial loading on the rotor including the compressor and turbine resulting from cooling air pressure in the compartment between the compressor and turbine is balanced by making the compressor and turbine areas exposed to the cooling air of equal area as by having the seals at compressor and turbine ends of the compartment equal in radius with respect to the air of the rotor.
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Citations
3 Claims
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1. A gas turbine construction in which the air thrust pressures on the rotor are balanced including:
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a compressor disk having a row of blades thereon, a turbine disk having a row of blades thereon, a shaft connecting said disks and having a conical portion adjacent to the compressor disk and forming, with said disks, the rotor, a first seal carried by said conical portion, a fixed seal cooperating with said first seal, a second seal carried by the turbine disk, a fixed second seal cooperating with said second seal, a bearing for the shaft between the disks, a housing surrounding said bearing, a structure surrounding said housing and defining a compartment extending between the compressor and turbine disks and having as a part of the boundry thereof the conical portion of the shaft radially inward of the first seal and, as another part, the portion of the turbine disk radially inward of the second seal, and means for pressurizing the compartment wherein an inner wall of combustion chamber, a support extending from said inner wall to the housing to maintain it in relation to the inner wall and holes in said support to balance the pressure on opposite sides thereof, wherein the first and second seal are at substantially the same radius with respect to the rotor thereby to expose substantially the same area to the pressure in said compartment. - View Dependent Claims (2, 3)
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Specification
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Current AssigneeUnited Technologies Corporation (Rtx Corporation)
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Original AssigneeUnited Technologies Corporation (Rtx Corporation)
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InventorsSchwarz, Frederick M., Neal, William F., Brown, Wayne M.
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Primary Examiner(s)Garrett, Robert E.
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Assistant Examiner(s)Kwon, John
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Application NumberUS06/681,332Time in Patent Office1,027 DaysField of Search415/104, 415/105, 415/106, 415/107, 415/96, 415/98, 415/102, 416/95US Class Current415/104CPC Class CodesF01D 3/00 Machines or engines with ax...
