Back to results
US 7,726,937 B2Granted
Turbine engine compressor vanes
AssigneeUnited Technologies Corporation
InventorsP. William Baumann, Om Parkash Sharma, Charles R. LeJambre, Sanjay S. Hingorani
Life of this patent
Estimating the term…
Abstract
A gas turbine engine rotor stack includes one or more longitudinally outwardly concave spacers. Outboard surfaces of the spacers may be in close facing proximity to inboard tips of vane airfoils. The airfoils have dihedral and sweep.
Claims24
A turbine engine comprising:
- a rotor comprising:
- a plurality of disks, each disk extending radially from an inner aperture to an outer periphery;
- a plurality of stages of blades, each stage borne by an associated one of said disks;
- and
- a plurality of spacers, each spacer between an adjacent pair of said disks;
- and
- a stator comprising a plurality of stages of vanes, the vanes of at least a first of said stages of vanes having airfoils with:
- inboard tips in facing proximity to an outer surface of a first of said spacers;
- and
- a dihedral and sweep profile characterized by:
- leading edge sweep of 25-45° along a first region of at least 10% of total span starting within 5% of the tip;
- and
- dihedral of 30-60° along a second region of at least 10% of total span staffing within 5% of the tip.
10 more elements
A gas turbine engine stator component comprising:
- a shroud or a shroud segment;
- at least one airfoil unitarily formed with or secured to the shroud or shroud segment and having:
- leading and trailing edges;
- pressure and suction sides;
- a proximal outboard root;
- a distal inboard tip;
- and
- a dihedral and sweep profile characterized by:
- leading edge sweep of 25-45° along a first region of at least 10% of total span starting within 5% of the tip;
- and
- dihedral of 30-60° along a second region of at least 10% of total span staffing within 5% of the tip.
8 more elements
A turbine engine vane element comprising:
- an outboard shroud having outboard and inboard surfaces the inboard surface being concave in a first direction so as to essentially define a longitudinal axis of curvature;
- and
- an airfoil element having:
- a root at the shroud inboard surface;
- a tip;
- and
- a dihedral and sweep profile characterized by:
- leading edge sweep of 25-45° along a first region of at least 10% of total span starting within 5% of the tip;
- and
- dihedral of 30-60° along a second region of at least 10of total span starting within 5% of the tip.
7 more elements
For a gas turbine engine configuration comprising:
- a rotor stack comprising:
- a plurality of disks, each disk extending radially from an inner aperture to an outer blade-bearing periphery;
- and
- a plurality of spacers, each spacer between an adjacent pair of said disks;
- a plurality of vane stages interspersed with the disks;
- and
- a shaft carrying the rotor stack,
- a method for engineering the engine configuration comprising:
- for at least a first of said vane stages varying a dihedral and sweep distribution to a final distribution characterized by:
- leading edge sweep of 25-45° along a first region of at least 10% of total span starting within 5% of the tip;
- and
- dihedral of 30-60° along a second region of at least 10 of total span starting within 5% of the tip.
9 more elements
A turbine engine comprising:
- a rotor comprising:
- a plurality of disks, each disk extending radially from an inner aperture to an outer periphery;
- a plurality of stages of blades, each stage borne by an associated one of said disks;
- and
- a plurality of spacers, each spacer between an adjacent pair of said disks;
- and
- a stator comprising a plurality of stages of vanes, the vanes of at least a first of said stages of vanes having airfoils with:
- inboard tips in facing proximity to an outer surface of a first of said spacers;
- and
- a dihedral and sweep profile characterized by at least one of:
- leading edge sweep of 25-45° along a first region of at least 10% of total span starting within 5% of the tip;
- and
- dihedral of 30-60° along a second region of at least 10% of total span starting within 5% of the tip, and
- wherein:
- said first spacer has a longitudinal cross-section, said longitudinal cross-section having a first portion being essentially outwardly concave in a static condition;
- and
- a central shaft carries the plurality of disks and the plurality of spacers to rotate about an axis with the plurality of disks and the plurality of spacers.
14 more elements
A turbine engine comprising:
- a rotor comprising:
- a plurality of disks, each disk extending radially from an inner aperture to an outer periphery;
- a plurality of stages of blades, each stage borne by an associated one of said disks;
- and
- a plurality of spacers, each spacer between an adjacent pair of said disks;
- and
- a stator comprising a plurality of stages of vanes, the vanes of at least a first of said stages of vanes having airfoils with:
- inboard tips in facing proximity to an outer surface of a first of said spacers, the inboard tips being longitudinally convex;
- and
- a dihedral and sweep profile characterized by at least one of:
- leading edge sweep of 25-45° along a first region of at least 10% of total span starting within 5% of the tip;
- and
- dihedral of 30-60° along a second region of at least 10% of total span starting within 5% of the tip.
10 more elements
Dependencies are inferred from the claim text.