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US 12,742,419 B1Granted
Turbine engine having a compression section
AssigneeGeneral Electric Company
InventorsBrandon Wayne Miller, Scott Alan Schimmels, Mark Gregory Wotzak, Jeffrey Donald Clements
Life of this patent
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Abstract
A turbine engine has an engine core, a plurality of axially arranged stages, an interstage cavity and a cooling airflow circuit. The engine core has a compression section, a combustion section and a turbine section. The plurality of axially arranged stages within the compression section have a low pressure (LP) set of stages and high pressure (HP) set of stages. The HP set of stages include a first HP stage and a second HP stage. The interstage cavity is formed between the first HP stage and the second HP stage. The cooling air circuit extends between the set of LP stages and the interstage cavity.
Claims20
A turbine engine defining an engine centerline, the turbine engine comprising:
- an engine core having a compression section, a combustion section, and a turbine section in serial flow arrangement, the engine core having a rotor portion rotatable about the engine centerline, the engine core defining a working airflow path through which a working airflow passes;
- a plurality of axially arranged stages located within the compression section, with each stage of the plurality of axially arranged stages having a set of circumferentially spaced blades extending through a respective portion of the working airflow path, the plurality of axially arranged stages having a set of low pressure (LP) stages and a set of high pressure (HP) stages, the set of HP stages having:
- a first HP stage including a first rotatable disk;
- and
- a second HP stage disposed axially adjacent to the first HP stage, the second HP stage having a second rotatable disk, the second rotatable disk having a main body, the first rotatable disk and the second rotatable disk axially forming an interstage cavity therebetween, the interstage cavity being locally fluidly isolated from the respective portion of the working airflow path that includes the set of circumferentially spaced blades of the first HP stage and the second HP stage;
- a cooling airflow circuit extending from a portion of the turbine engine upstream of the first HP stage and the second HP stage and opening to the interstage cavity;
- and
- a set of fins located within the interstage cavity, the set of fins being rotatable with the rotor portion to impart circulation to a flow of fluid within the interstage cavity from the cooling airflow circuit.
5 more elements
A turbine engine defining an engine centerline, the turbine engine comprising:
- an engine core having a compression section, a combustion section, and a turbine section in serial flow arrangement, the engine core having a rotor portion rotatable about the engine centerline, the engine core defining a working airflow path through which a working airflow passes;
- a plurality of axially arranged stages located within the compression section, with each stage of the plurality of axially arranged stages having a set of circumferentially spaced blades, the plurality of axially arranged stages having a set of low pressure (LP) stages and a set of high pressure (HP) stages, the set of HP stages having:
- a first HP stage including a first rotatable disk;
- and
- a second HP stage disposed axially adjacent to the first HP stage, the second HP stage having a second rotatable disk, the second rotatable disk having a main body, the first rotatable disk and the second rotatable disk axially forming an interstage cavity therebetween, the interstage cavity being at least locally fluidly isolated from the working airflow path within the second HP stage;
- a cooling airflow circuit extending from a portion of the turbine engine upstream of the interstage cavity and opening to the interstage cavity;
- and
- a set of fins located within the interstage cavity, the set of fins being rotatable with the rotor portion to impart circulation to a flow of fluid within the interstage cavity from the cooling airflow circuit wherein each fin of the set of fins comprise a suction side and a pressure side.
5 more elements
A turbine engine defining an engine centerline, the turbine engine comprising:
- an engine core having a compression section, a combustion section, and a turbine section in serial flow arrangement, the engine core having a rotor portion rotatable about the engine centerline, the engine core defining a working airflow path through which a working airflow passes;
- a plurality of axially arranged stages located within the compression section, with each stage of the plurality of axially arranged stages having a set of circumferentially spaced blades, the plurality of axially arranged stages having a set of low pressure (LP) stages and a set of high pressure (HP) stages, the set of HP stages having:
- a first HP stage including a first rotatable disk;
- and
- a second HP stage disposed axially adjacent to the first HP stage, the second HP stage having a second rotatable disk, the second rotatable disk having a main body, the first rotatable disk and the second rotatable disk axially forming an interstage cavity therebetween, the interstage cavity being at least locally fluidly isolated from the working airflow path within the second HP stage;
- a cooling airflow circuit extending from a portion of the turbine engine upstream of the interstage cavity and opening to the interstage cavity;
- and
- a set of fins located within the interstage cavity, the set of fins being rotatable with the rotor portion to impart circulation to a flow of fluid within the interstage cavity from the cooling airflow circuit;
- wherein at least one of:
- at least a first group of the set of fins are located along the first rotatable disk, with each fin of the set of fins including a leading edge and a trailing edge, with the first group of the set of fins being arranged such that the leading edge is radially inward from the trailing edge;
- or
- at least a second group of the set of fins are located along the second rotatable disk, with each fin of the set of fins including a leading edge and a trailing edge, with at least the second group of the set of fins being arranged such that the leading edge is radially outward from the trailing edge.
9 more elements
Dependencies are inferred from the claim text.