Fastener openings for stress distribution

Patent metadata

Field	Value
Publication number	US-10823012-B2
Application number	US-201615160990-A
Country	US
Kind code	B2
Filing date	May 20, 2016
Priority date	May 20, 2016
Publication date	Nov 3, 2020
Grant date	Nov 3, 2020

Abstract

A structure configured to rotate about an axis may include a fastener opening defined in a surface of the structure. The fastener opening may extend through the surface and include a circular portion, a first slot portion, and a second slot portion. The circular portion may include a first radius of curvature. The first slot portion may extend from the circular portion circumferentially relative to the axis. The second slot portion may also extend from the circular portion circumferentially relative to the axis.

First claim

What is claimed is:

1. A mating structure, comprising:
a fastener opening defined by the mating structure and extending through the mating structure, wherein the fastener opening comprises:
a circular portion defined by the mating structure and comprising a first radius of curvature,
a first slot portion located in the mating structure, defined by radially spaced proximal and distal walls, and extending from the circular portion, the first slot portion continuous with the circular portion,
an end portion on the first slot portion, the end portion comprising a second radius of curvature less than the first radius of curvature, and
a second slot portion located in the mating structure, defined by radially spaced proximal and distal walls, and extending from the circular portion, the second slot portion comprising a third radius of curvature less than the first radius of curvature, wherein the circular portion is located between the first slot portion and the second slot portion, wherein the mating structure comprises a gas turbine rotor body, wherein the first slot portion and the second slot portion comprise a curvature defined by a radius extending from a center of one of the first slot portion or the second slot portion to an engine central longitudinal axis, and wherein the circular portion, the first slot portion, and the second slot portion are defined in a single plane perpendicular to the central longitudinal axis.

2. The mating structure of claim 1 , wherein the proximal and distal walls defining the first slot portion are tangential to a second wall of the mating structure defining the end portion.

3. The mating structure of claim 2 , wherein the circular portion is configured to retain a fastener.

4. The mating structure of claim 2 , wherein the first slot portion and the second slot portion comprise a uniform width.

5. A structure configured to rotate about an axis, comprising:
a fastener opening comprising:
a circular portion defined by the structure and comprising a first radius of curvature,
a first slot portion located in the structure, defined by radially spaced proximal and distal walls, and extending from the circular portion circumferentially relative to the axis, the first slot portion continuous with the circular portion,
an end portion on the first slot portion comprising a second radius of curvature less than the first radius of curvature, wherein the proximal and distal walls defining the first slot portion are tangential to a second wall of the structure defining the end portion, and
a second slot portion located in the structure, defined by radially spaced proximal and distal walls, and extending from the circular portion circumferentially relative to the axis, the second slot portion comprising a third radius of curvature less than the first radius of curvature, wherein the first slot portion joins the circular portion opposite the second slot portion, wherein the structure comprises a gas turbine rotor body, wherein the first slot portion and the second slot portion comprise a curvature defined by a radius extending from a center of one of the first slot portion or the second slot portion to the axis, and wherein the circular portion, the first slot portion, and the second slot portion are defined in a single plane perpendicular to the axis.

6. The structure of claim 5 , wherein the circular portion is configured to retain a fastener radially relative to the axis.

7. The structure of claim 6 , wherein the circular portion is configured to retain the fastener circumferentially relative to the axis.

8. The structure of claim 5 , wherein the first slot portion and the second slot portion comprise a uniform width in a radial direction relative to the axis.

9. The structure of claim 8 , wherein a radial surface of the structure comprises a tapered surface disposed around at least a portion of the fastener opening.

10. A rotating component of a gas turbine engine, comprising:
a rotor of a compressor section configured to rotate about an axis;
a rotating structure adjacent the rotor;
a fastener passing through a fastener opening defined by at least one of the rotor or the rotating structure, wherein the fastener opening comprises:
a circular portion comprising a first radius of curvature and configured to retain the fastener circumferentially relative to the axis,
a first slot portion defined by radially spaced proximal and distal walls and extending from the circular portion circumferentially relative to the axis, the first slot portion continuous with the circular portion,
an end portion on the first slot portion comprising a second radius of curvature less than the first radius of curvature, wherein the proximal and distal walls defining the first slot portion are tangential to a second wall of the end portion, and
a second slot portion defined by radially spaced proximal and distal walls and extending from the circular portion circumferentially relative to the axis, the second slot portion comprising a third radius of curvature less than the first radius of curvature, wherein the circular portion is located between the first slot portion and the second slot portion,

wherein the first slot portion and the second slot portion comprise a curvature defined by a radius extending from a center of one of the first slot portion or the second slot portion to the axis, and wherein the circular portion the first slot portion, and the second slot portion are defined in a single plane perpendicular to the axis.

11. The rotating component of claim 10 , wherein the first slot portion and the second slot portion comprise a uniform width in a radial direction relative to the axis.

12. The rotating component of claim 11 , wherein the uniform width of the first slot portion and the second slot portion is less than a diameter of the circular portion.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Hendrickson Timothy
• Dorer James

Classifications

• F01D5/025 Primary

  Fixing blade carrying members on shafts (attachment of a member on a shaft in general F16D1/06; for non-positive displacement pumps F04D29/00) · CPC title

• F16B31/06

  having regard to possibility of fatigue rupture · CPC title

• F05D2260/36

  by a form fit connection, e.g. by interlocking · CPC title

• F01D25/28 Primary

  Supporting or mounting arrangements, e.g. for turbine casing · CPC title

• F01D5/066

  Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps · CPC title