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US 12,760,653 B1Granted
Stator platform seal augmentation
AssigneeRtx Corporation
InventorsJacob Kyle Yochimowitz, Farruqh Shahab, Andrew R. Dolan, Mitch Eddington Blimmel
Life of this patent
Estimating the term…
Abstract
A gas turbine engine stator stage has: an inner diameter platform; an outer diameter shroud; and a plurality of airfoils extending between the platform and shroud. The platform has an axially forward end and an axially aft end and an inner diameter (ID) surface. At least one of the platform forward end, aft end, and inner diameter (ID) surface bears a swirl generator for inducing swirl in a leakage flow passing radially inward behind the aft end and forward and then radially outward past the forward end.
Claims20
A gas turbine engine comprising:
- a rotor having a first blade stage and a second blade stage each having a disk;
- a stator having a vane stage between the first blade stage and the second blade stage and having a platform;
- and
- a sealing system having a stator section and a rotor section,
- wherein:
- the platform has an outer diameter (OD) gaspath surface from which airfoils of the vane stage extend, a forward end, an aft end, and an inner diameter (ID) surface;
- the sealing system rotor section comprises one or more radially outwardly protruding features on the rotor section;
- the sealing system stator section comprises one or more lands mounted to the platform inner diameter surface;
- each of the lands have an outer diameter (OD) surface mounted to the platform and an aft surface;
- and
- each land aft surface has a concavity leading radially inward to an aftward protrusion spaced from the platform ID surface.
8 more elements
A gas turbine engine stator stage comprising:
- a plurality of vane segments each having:
- an inner diameter platform;
- an outer diameter shroud;
- and
- one or more airfoils extending between the platform and shroud;
- and
- wherein:
- the platforms each have an axially forward end and an axially aft end;
- the platforms each have a first circumferential end section and a second circumferential end section;
- the second end sections are received in the first end sections of adjacent platforms;
- and at least one of:
- a) a forward swirler is mounted to the platform forward end and has a first face facing the forward end, a second face spaced forwardly of the first face, an inner diameter (ID face) and an outer diameter (OD) face, the second face having a forward and radially inward concavity;
- b) a forward swirler is mounted to the platform forward end and has a first face facing the forward end, a second face spaced forwardly of the first face, an inner diameter (ID face) and an outer diameter (OD) face, the ID face having a rearward and radially inward concavity;
- c) an aft swirler is mounted to the platform aft end and has a first face facing the aft end and second face spaced aft of the first face, an inner diameter (ID face) and an outer diameter (OD) face, the OD face having a forward and radially outward concavity;
- d) an aft swirler is mounted to the platform aft end and has a first face facing the aft end and second face spaced aft of the first face, an inner diameter (ID face) and an outer diameter (OD) face, the second face having a rearward and radially outward concavity;
- and
- e) an inner diameter (ID) swirler is formed as a seal land mounted to an inner diameter (ID) surface of the platform and has a first face facing the inner ID surface of the platform and second face spaced radially inward of the first face, an aft face, and a forward face, the aft face having an aftward and radially outward concavity.
14 more elements
A gas turbine engine stator stage comprising:
- an inner diameter platform;
- an outer diameter shroud;
- and
- a plurality of airfoils extending between the platform and shroud;
- and
- wherein:
- the platform has an axially forward end and an axially aft end and an inner diameter (ID) surface;
- and
- at least one of the platform forward end, aft end, and inner diameter (ID) surface bears means for inducing swirl in a leakage flow passing radially inward behind the aft end and forward and then radially outward past the forward end.
6 more elements
Dependencies are inferred from the claim text.