Patent Application
20250067191
Exemplary embodiments pertain to the art of gas turbine engines, and in particular to balancing of turbine rotors and rotor assemblies of gas turbine engines.
Cavities in gas turbine engines, for example, cavities between turbine rotors, need to be sealed to ensure a proper air pressure distribution along the gas turbine engine flow path. Seals are utilized at interstage locations in the turbine assembly located radially between a rotating component such as a turbine rotor, and a stationary component such as a turbine stator. Further, the turbine rotors require balancing as a component, and as part of a turbine assembly in order to ensure performance characteristics of the gas turbine engine.
In one exemplary embodiment, a rotor of a gas turbine engine includes a rotor hub rotatable about a rotor central axis, a plurality of rotor blades extending radially outwardly from the rotor hub, and a rotor flange extending axially from the rotor hub. The rotor flange at least partially defines a seal assembly configured to seal between the rotor and a static structure of the gas turbine engine, and a rotor balancing structure configured to rotationally balance the rotor.
Additionally or alternatively, in this or other embodiments the seal assembly includes a labyrinth seal having a seal base positioned at the rotor flange, and a plurality of seal fins extending from the seal base toward the static structure to define a seal interface between the plurality of seal fins and the static structure.
Additionally or alternatively, in this or other embodiments the plurality of seal fins extend radially outwardly from the rotor flange.
Additionally or alternatively, in this or other embodiments the rotor balancing structure includes a balancing flange extending from the rotor flange.
Additionally or alternatively, in this or other embodiments the balancing flange extends radially inwardly from the rotor flange.
Additionally or alternatively, in this or other embodiments the balancing flange extends from an axial end of the rotor flange.
Additionally or alternatively, in this or other embodiments the rotor balancing structure further includes one or more counterweights secured to the balancing flange.
In another exemplary embodiment, a turbine of a gas turbine engine includes a turbine static structure, and a turbine rotor located at and rotatable about a turbine central axis. The turbine rotor includes a turbine rotor hub located at the turbine central axis, a plurality of rotor blades extending radially outwardly from the turbine rotor hub, and a turbine rotor flange extending axially from the turbine rotor hub. The turbine rotor flange at least partially defines a seal assembly configured to seal between the turbine rotor and the turbine static structure, and a rotor balancing structure configured to rotationally balance the turbine rotor.
Additionally or alternatively, in this or other embodiments the seal assembly includes a labyrinth seal having a seal base positioned at the turbine rotor flange, and a plurality of seal fins extending from the seal base toward the static structure to define a seal interface between the plurality of seal fins and the turbine static structure.
Additionally or alternatively, in this or other embodiments the plurality of seal fins extend radially outwardly from the turbine rotor flange.
Additionally or alternatively, in this or other embodiments the rotor balancing structure includes a balancing flange extending from the turbine rotor flange.
Additionally or alternatively, in this or other embodiments the balancing flange extends radially inwardly from the turbine rotor flange.
Additionally or alternatively, in this or other embodiments the balancing flange extends from an axial end of the turbine rotor flange.
Additionally or alternatively, in this or other embodiments the rotor balancing structure further includes one or more counterweights secured to the balancing flange.
Additionally or alternatively, in this or other embodiments the turbine stating structure is a turbine frame.
In yet another exemplary embodiment, a gas turbine engine includes a combustor configured to combust a mixture of air and fuel, and a turbine assembly including a turbine rotor driven to rotate about an engine central axis by a flow of combustion gases from the combustor. The turbine rotor includes a turbine rotor hub located at the turbine central axis, a plurality of rotor blades extending radially outwardly from the turbine rotor hub, and a turbine rotor flange extending axially from the turbine rotor hub. The turbine rotor flange at least partially defines a seal assembly configured to seal between the turbine rotor and a turbine static structure, and a rotor balancing structure configured to rotationally balance the turbine rotor.
Additionally or alternatively, in this or other embodiments the seal assembly includes a labyrinth seal having a seal base located at the turbine rotor flange, and a plurality of seal fins extending from the seal base toward the static structure to define a seal interface between the plurality of seal fins and the turbine static structure.
Additionally or alternatively, in this or other embodiments the plurality of seal fins extend radially outwardly from the turbine rotor flange.
Additionally or alternatively, in this or other embodiments the rotor balancing structure includes a balancing flange extending radially inwardly from the turbine rotor flange.
Additionally or alternatively, in this or other embodiments the rotor balancing structure further includes one or more counterweights secured to the balancing flange.
The following descriptions should not be considered limiting in any way. With reference to the accompanying drawings, like elements are numbered alike:
A detailed description of one or more embodiments of the disclosed apparatus and method are presented herein by way of exemplification and not limitation with reference to the Figures.
Illustrated in
The hot section 14 includes a combustor 26 at which compressed airflow output from the compressor 18 is mixed with a fuel and combusted, producing hot combustion gases 28, which are directed to a turbine 30. The turbine 30 includes one or more turbine rotors 32 rotatable about the engine central axis 22 and one or more turbine stators 34 located axially adjacent to the one or more turbine rotors 32. The turbine rotors 32 include a plurality of turbine blades 36 fixed to a rotor hub 38. The one or more turbine stators 34 are fixed relative to the engine central axis 22 and include a plurality of stator vanes 40. The hot combustion gases 28 drive rotation of the turbine rotors 32, which drives rotation of the compressor rotor 20 and provides thrust for the gas turbine engine 10.
Referring to
A seal assembly 44 is positioned at the rotor flange 42. In the embodiment of
In other embodiments, the seal assembly 44 may be another configuration, for example, such as a brush seal assembly 44 as illustrated in
Referring again to
Combining the sealing functions and balancing functions into the same rotor flange 42 via the seal assembly 44 and the balancing flange 60 reduces the axial space occupied by the turbine rotor 32, and reduces complexity of the turbine rotor 32. Further, this allows for optimal radial position of both the seal assembly 44 and the balancing flange 60. Additionally, while the present description present the features in the context of a turbine rotor 32, one skilled in the art will appreciate that the configurations of the present disclosure may be similarly applied to other rotating components such as compressor rotors 20.
The term “about” is intended to include the degree of error associated with measurement of the particular quantity based upon the equipment available at the time of filing the application.
The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the present disclosure. As used herein, the singular forms “a”, “an” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms “comprises” and/or “comprising,” when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, element components, and/or groups thereof.
While the present disclosure has been described with reference to an exemplary embodiment or embodiments, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the scope of the present disclosure. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the present disclosure without departing from the essential scope thereof. Therefore, it is intended that the present disclosure not be limited to the particular embodiment disclosed as the best mode contemplated for carrying out this present disclosure, but that the present disclosure will include all embodiments falling within the scope of the claims.
