Flange stress-reduction features
A flange includes a flange body annularly disposed about a longitudinal axis. The flange body includes a first radial side and a second radial side radially opposite the first radial side. The flange body defines a first fastener hole and a circumferentially adjacent second fastener hole formed through the flange body. A first shielding zone has at least a portion of the first shielding zone located between the first and second fastener holes. A first shielding feature is disposed in the first shielding zone.
1. A gas turbine engine comprising:
a first case;
a first flange comprising:
a flange body annularly disposed about a longitudinal centerline of the gas turbine engine and comprising a first radial side and a second radial side, the flange body extending radially from the first radial side to the second radial side, and the flange body defining a first fastener hole and a circumferentially adjacent second fastener hole formed through the flange body, wherein the flange body is connected to the first case at the first radial side and the first flange projects radially out from the first case in a first radial direction, a circumferential centerline extends circumferentially about the longitudinal centerline, the circumferential centerline bisects the first fastener hole dividing the first fastener hole into two equal first fastener hole parts, the circumferential centerline bisects the second fastener hole dividing the second fastener hole into two equal second fastener hole parts;
a first shielding zone, at least a portion of the first shielding zone located between the first and second fastener holes; and
a first shielding feature disposed in the first shielding zone, the first shielding feature located radially between and displaced radially away from the circumferential centerline and the first radial side, the first shielding feature comprising an aperture with a circular cross-sectional geometry, and a center point of the aperture radially displaced from the circumferential centerline;
a second case; and
a second flange connected to the second case, the second flange projecting radially out from the second case in the first radial direction, and the second flange mechanically attached to the first flange.
2. The gas turbine engine of claim 1 , wherein
the flange body comprises a first radial portion and a second radial portion radially adjacent the first radial portion;
the circumferential centerline forms a boundary line between the first radial portion and the second radial portion; and
the first shielding zone is disposed within the first radial portion.
3. The gas turbine engine of claim 1 , wherein the first flange is within at least one of a combustor section or a turbine section of the gas turbine engine.
4. The gas turbine engine of claim 1 , wherein the aperture extends axially through the flange body.
5. The gas turbine engine of claim 1 , further comprising
a first bolt projecting through the first fastener hole and mechanically attaching the first flange with the second flange; and
a second bolt projecting through the second fastener hole and mechanically attaching the first flange with the second flange.
6. A gas turbine engine apparatus, comprising:
a first case;
a first flange integrally formed with the first case, the first flange projecting radially out from the first case in a first radial direction, and the first flange comprising:
a flange body annularly disposed about a longitudinal centerline of the gas turbine engine apparatus, the flange body comprising a first radial side and a second radial side, the flange body extending radially between the first radial side and the second radial side, and the flange body forming a first fastener hole and a second fastener hole formed through the flange body, the second fastener hole circumferentially adjacent the first fastener hole, wherein a circumferential centerline extends circumferentially about the longitudinal centerline and bisects the first fastener hole and the second fastener hole;
a first shielding zone, at least a portion of the first shielding zone located between the first fastener hole and the second fastener hole; and
a first shielding feature disposed in the first shielding zone, the first shielding feature comprising an aperture with a circular cross-sectional geometry, and a center point of the aperture radially displaced from the circumferential centerline;
a second case; and
a second flange integrally formed with the second case, the second flange projecting radially out from the second case in the first radial direction, and the second flange mechanically attached to the first flange.
7. The gas turbine engine apparatus of claim 6 , further comprising
a first bolt projecting through the first fastener hole and mechanically attaching the first flange and the second flange together; and
a second bolt projecting through the second fastener hole and mechanically attaching the first flange and the second flange together.
8. The gas turbine engine apparatus of claim 6 , wherein the first case is an outer diffuser case.
9. The gas turbine engine apparatus of claim 6 , wherein the first case is a high-pressure turbine case.