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US 2019/0284936 A1Published application
Gas turbine engine rotor disk
AssigneeUnited Technologies Corporation
InventorRyan Hamilton Quinn
Life of this patent
Estimating the term…
Abstract
A rotor disk includes a web that extends in a radial direction from a rim on a radially outer end to a bore on a radially inner end. The web includes a mismatch protrusion on a first axially facing surface of the web. A balancing protrusion is on a second axially facing surface of the web.
Claims20
A rotor disk comprising:
- a web extending in a radial direction from a rim on a radially outer end to a bore on a radially inner end, the web including:
- a mismatch protrusion on a first axially facing surface of the web;
- and
- a balancing protrusion on a second axially facing surface of the web.
1 more element
A gas turbine engine comprising:
- a compressor section;
- and
- a turbine section located downstream of the compressor section, wherein at least one of the compressor section or the turbine section includes a rotor disk including:
- a web extending in a radial direction from a rim on a radially outer end to a bore on a radially inner end, the web including:
- a mismatch protrusion on a first axially facing surface of the web;
- and
- a balancing protrusion on a second axially facing surface of the web.
4 more elements
A method of forming rotor disk for a gas turbine engine comprising the steps of:
- machining a first mismatch web surface on a first axial side of the web;
- and
- machining a second mismatch web surface on the first axial side of the web, wherein a mismatch plateau separates the first mismatch web surface from the second mismatch web surface.
Dependencies are inferred from the claim text.