Intermittent spigot joint for gas turbine engine casing connection

Patent metadata

Field	Value
Publication number	US-11009039-B2
Application number	US-201816226694-A
Country	US
Kind code	B2
Filing date	Dec 20, 2018
Priority date	Feb 18, 2016
Publication date	May 18, 2021
Grant date	May 18, 2021

Abstract

A gas turbine engine casing apparatus includes annular first and second annular cases connected by a spigot joint. The spigot joint includes an annular projection of the first annular case fitted into an annular recess of the second annular case. A plurality of circumferentially spaced apart scallops are formed on one of surfaces of the annular projection or of the annular recess, and are located in selective circumferential locations adjacent respective enhanced stiff areas of the first and second annular cases.

First claim

The invention claimed is:

1. A gas turbine engine casing assembly, comprising:
a first annular case having a central axis and an annular seat at one of a front end and a rear end of the first annular case,
the annular seat having an annular surface facing toward the central axis and a surface angled relative to the central axis;

a second annular case connected coaxially to the first annular case and having an annular projection received in the annular seat, the annular projection having:
a surface contacting the surface angled relative to the central axis of the annular seat, and
an annular surface engaging the annular surface of the annular seat at a plurality of locations that are distributed circumferentially along the annular surface of the annular seat; and

a plurality of scallops circumferentially spaced from one another and formed on at least one of the annular surface of the annular projection and the annular surface of the annular seat, a given scallop of the plurality of scallops being between a given pair of locations of the plurality of locations, wherein at least one of the scallops is located symmetrically about a radial central axis of a structural member projecting from the at least one of the annular surface of the annular projection and the annular surface of the annular seat.

2. The gas turbine engine casing assembly of claim 1 , further comprising a plurality of fasteners extending through the annular seat and the annular projection at respective locations distributed circumferentially along the annular surface of the annular seat.

3. The gas turbine engine casing assembly of claim 2 , wherein the annular surface of the annular seat and the annular surface of the annular projection are disposed radially outward of the plurality of fasteners.

4. The gas turbine engine casing assembly of claim 1 , wherein the structural member is a strut.

5. The gas turbine engine casing assembly of claim 1 , wherein at least one scallop of the plurality of scallops is arcuate.

6. The gas turbine engine casing assembly of claim 1 , wherein the annular surface of the annular seat is disposed radially outward of the annular surface of the annular projection relative to the central axis.

7. The gas turbine engine casing assembly of claim 6 , wherein the annular projection includes a second surface that faces toward the central axis and is disposed radially inward of the annular surface of the annular projection, and the annular seat includes a second surface that contacts the second surface of the annular projection.

Assignees

• Pratt & Whitney Canada

Inventors

• Veitch Thomas
• Urac Tibor
• Richardson Tyler

Classifications

• F01D25/243

  Flange connections; Bolting arrangements (F01D25/265 takes precedence) · CPC title

• F01D25/162 Primary

  Bearing supports · CPC title

• F04D29/284

  for compressors · CPC title

• F04D29/644

  especially adapted for elastic fluid pumps · CPC title

• F04D29/526 Primary

  Details of the casing section radially opposing blade tips (ducts F04D29/545) · CPC title