Split intermediate case

Patent metadata

Field	Value
Publication number	US-10287979-B2
Application number	US-201213674342-A
Country	US
Kind code	B2
Filing date	Nov 12, 2012
Priority date	Nov 12, 2012
Publication date	May 14, 2019
Grant date	May 14, 2019

Abstract

An intermediate case (IMC) for use in a compressor section of a gas turbine engine includes a bleed duct and an IMC centerbody. The bleed duct is formed via sand casting. The IMC centerbody is formed via investment casting and is fixedly attached to the bleed duct.

First claim

The invention claimed is:

1. A gas turbine engine comprising:
a first compressor;
a second compressor;
an intermediate case (IMC) positioned between the first compressor and the second compressor, the intermediate case comprising:
a bleed duct formed via sand casting, wherein the bleed duct comprises:
a front section extending upstream toward the first compressor in a substantially axial direction with respect to a centerline axis of the gas turbine engine;
a trailing edge disposed downstream of the front section;
a plurality of bleed duct outlets extending radially outward through the front section of the bleed duct and positioned axially upstream from the trailing edge; and
a flange connected to the trailing edge, wherein the flange extends radially outward beyond the front section and beyond the plurality of bleed duct outlets relative a centerline axis of the gas turbine engine; and

an IMC centerbody formed via investment casting and fixedly attached to the trailing edge of the bleed duct, wherein the IMC centerbody extends downstream from the trailing edge of the bleed duct.

2. The gas turbine engine of claim 1 , wherein the IMC centerbody comprises:
an inner diameter case;
an outer diameter case; and
a plurality of struts extending from the inner diameter case to the outer diameter case.

3. The gas turbine engine of claim 1 , wherein the bleed duct is connected to the IMC centerbody via an interference fit and bolts.

4. The gas turbine engine of claim 1 , wherein the bleed duct is a 2.5 bleed duct.

5. The gas turbine engine of claim 1 , wherein the gas turbine engine is an industrial gas turbine engine.

6. The gas turbine engine of claim 5 , and further comprising:
a first turbine connected to the first compressor via a first shaft;
a second turbine connected to the second compressor via a second shaft; and
a power turbine positioned axially aft of the first and second turbines.

7. The gas turbine engine of claim 1 , and further comprising:
a collector box connected to the flange of the bleed duct for receiving bleed air flowing through the bleed duct outlets.

8. An intermediate case (IMC) for use in a compressor section of a gas turbine engine, the IMC comprising:
a bleed duct, wherein the bleed duct comprises:
a front section extending in a substantially axial direction with respect to a centerline axis of the gas turbine engine;
a trailing edge disposed downstream of the front section;
a plurality of bleed duct outlets extending radially outward through the front section of the bleed duct and positioned axially upstream from the trailing edge; and
a flange connected to the trailing edge, wherein the flange extends radially outward beyond the front section and beyond the plurality of bleed duct outlets relative a centerline axis of the gas turbine engine; and

an IMC centerbody fixedly attached to the trailing edge of the bleed duct.

9. The IMC of claim 8 , wherein the bleed duct and the IMC centerbody are made of a substantially similar metal.

10. The IMC of claim 8 , wherein the bleed duct and the IMC centerbody are both made of 17-4 stainless steel.

11. A method for forming an intermediate case (IMC) for use in a compressor section of a gas turbine engine, the method comprising:
forming a bleed duct via sand casting, wherein the bleed duct comprises:
casting a front section extending in a substantially axial direction with respect to a centerline axis of the gas turbine engine;
casting a trailing edge disposed downstream of the front section;
forming a plurality of bleed duct outlets extending radially outward through the front section of the bleed duct and positioned axially upstream from the trailing edge; and
casting a flange connected to the trailing edge, wherein the flange extends radially outward beyond the front section and beyond the plurality of bleed duct outlets relative a centerline axis of the gas turbine engine;

forming an IMC centerbody by investment casting; and
fixedly attaching the IMC centerbody to the trailing edge of the bleed duct.

12. The method of claim 11 , wherein forming the bleed duct via sand casting comprises:
packing sand around a reusable pattern;
solidifying the sand to form a sand mold;
removing the reusable pattern from the sand mold;
filling the sand mold with molten metal; and
removing the sand mold after the molten metal solidifies.

13. The method of claim 11 , and further comprising:
machining the bleed duct after sand casting.

14. The method of claim 11 , wherein forming the IMC centerbody via investment casting comprises:
dipping a single use pattern into a ceramic material;
baking the ceramic material to form a ceramic mold;
heating the ceramic mold to liquefy the single use pattern;
filling the ceramic mold with molten metal; and
removing the ceramic mold after the molten metal solidifies.

15. The method of claim 14 , wherein forming the IMC centerbody via investment casting further comprises:
forming the single use pattern out of a polymer material via stereolithography.

16. The method of claim 11 , wherein the bleed duct and the IMC centerbody are formed of a substantially similar metal.

17. The method of claim 11 , wherein the bleed duct and the IMC centerbody are formed of 17-4 stainless steel.

18. The method of claim 11 , wherein fixedly attaching the IMC centerbody to the bleed duct comprises:
heating the bleed duct to cause the bleed duct to expand;
positioning the IMC centerbody at least partially inside the bleed duct; and
cooling the bleed duct to create an interference fit between the bleed duct and the IMC centerbody.

19. The method of claim 18 , wherein fixedly attaching the IMC centerbody to the bleed duct further comprises:
inserting bolts through the IMC centerbody and into the trailing edge of the bleed duct after creating the interference fit.

Assignees

• United Technologies Corp

Inventors

• Desfosses Brian
• Quin Willoughby Marshall

Classifications

• B22C9/02 Primary

  Sand moulds or like moulds for shaped castings · CPC title

• B22D25/02

  by its peculiarity of shape; of works of art {(cylinders, pistons B22D15/02)} · CPC title

• F02C6/08

  the gas being bled from the gas-turbine compressor · CPC title

• F04D29/023

  especially adapted for elastic fluid pumps · CPC title

• F04D17/025

  comprising axial flow and radial flow stages · CPC title