Air cycle machine turbine seal plate

Patent metadata

Field	Value
Publication number	US-9745858-B2
Application number	US-201514731523-A
Country	US
Kind code	B2
Filing date	Jun 5, 2015
Priority date	Jun 5, 2015
Publication date	Aug 29, 2017
Grant date	Aug 29, 2017

Abstract

A turbine seal plate includes an inner rim with a labyrinth seal land that defines a central bore having a labyrinth seal diameter. The turbine seal plate also includes a housing coupling ring arranged radially outward of the inner rim. A housing pilot extends axially from the housing coupling ring and substantially parallel to the labyrinth seal land with respect to a radially inner portion of the housing pilot. The housing pilot has a housing pilot thickness, and a ratio of the housing pilot thickness to the labyrinth seal diameter is between 0.08 and 0.14. A frusto-conical body extends between the radially inner portion of the housing pilot and the inner rim of the turbine seal plate.

First claim

What is claimed is:

1. A turbine seal plate for an air cycle machine, the turbine seal plate comprising:
an inner rim comprising a labyrinth seal land that defines a central bore having a labyrinth seal diameter;
a housing coupling ring arranged radially outward of the inner rim;
a housing pilot extending axially from the housing coupling ring and substantially parallel to the labyrinth seal land with respect to a radially inner portion of the housing pilot, wherein the housing pilot comprises a turbine housing pilot defined by a first radially outer portion of the housing pilot having a turbine housing pilot diameter, and the housing pilot further comprises a compressor housing pilot defined by a second radially outer portion of the housing pilot having a compressor housing pilot diameter, wherein the housing pilot has a housing pilot thickness, a ratio of the housing pilot thickness to the labyrinth seal diameter is between 0.08 and 0.14, a ratio of the housing pilot thickness to the turbine housing pilot diameter is between 0.0101 and 0.0177, and a ratio of the housing pilot thickness to the compressor housing pilot diameter is between 0.0102 and 0.0178; and
a frusto-conical body extending between the radially inner portion of the housing pilot and the inner rim.

2. The turbine seal plate according to claim 1 , wherein a ratio of the turbine housing pilot diameter to the labyrinth seal diameter is between 4.006 and 4.014.

3. The turbine seal plate according to claim 1 , wherein a ratio of the turbine housing pilot diameter to the compressor housing pilot diameter is between 1.001 and 1.003.

4. The turbine seal plate according to claim 1 , wherein a ratio of the labyrinth seal diameter to the compressor housing pilot diameter is between 0.249 and 0.251.

5. An air cycle machine assembly comprising:
a shaft;
a turbine housing;
a compressor housing; and
a turbine seal plate comprising:
an inner rim comprising a labyrinth seal land that defines a central bore having a labyrinth seal diameter, wherein the shaft forms a labyrinth seal with respect to the labyrinth seal land;
a housing coupling ring arranged radially outward of the inner rim, the housing coupling ring coupled to the turbine housing and the compressor housing;

a housing pilot that contacts the turbine housing and the compressor housing and extends axially from the housing coupling ring and substantially parallel to the labyrinth seal land with respect to a radially inner portion of the housing pilot, wherein the housing pilot comprises a turbine housing pilot defined by a first radially outer portion of the housing pilot having a turbine housing pilot diameter, and the housing pilot further comprises a compressor housing pilot defined by a second radially outer portion of the housing pilot having a compressor housing pilot diameter, wherein the housing pilot has a housing pilot thickness, a ratio of the housing pilot thickness to the labyrinth seal diameter is between 0.08 and 0.14, a ratio of the housing pilot thickness to the turbine housing pilot diameter is between 0.0101 and 0.0177, and a ratio of the housing pilot thickness to the compressor housing pilot diameter is between 0.0102 and 0.0178; and
a frusto-conical body extending between the radially inner portion of the housing pilot and the inner rim.

6. The air cycle machine assembly according to claim 5 , wherein a ratio of the turbine housing pilot diameter to the labyrinth seal diameter is between 4.006 and 4.014.

7. The air cycle machine assembly according to claim 5 , wherein a ratio of the turbine housing pilot diameter to the compressor housing pilot diameter is between 1.001 and 1.003.

8. The air cycle machine assembly according to claim 5 , wherein a ratio of the labyrinth seal diameter to the compressor housing pilot diameter is between 0.249 and 0.251.

9. A method of installing a turbine seal plate in an air cycle machine, comprising:
aligning a housing coupling ring of a turbine seal plate with a turbine housing and a compressor housing;
placing a turbine housing pilot of a housing pilot of the turbine seal plate in contact with the turbine housing and a compressor housing pilot of the housing pilot of the turbine seal plate in contact with the compressor housing, the housing pilot extending axially from the housing coupling ring and substantially parallel to a labyrinth seal land with respect to a radially inner portion of the housing pilot, wherein the turbine housing pilot is defined by a first radially outer portion of the housing pilot having a turbine housing pilot diameter and the compressor housing pilot is defined by a second radially outer portion of the housing pilot having a compressor housing pilot diameter;
coupling the turbine housing and the compressor housing to the turbine seal plate through the housing coupling ring; and
arranging a shaft within an inner rim of the turbine seal plate to form a labyrinth seal with respect to the labyrinth seal land, wherein the inner rim comprises the labyrinth seal land that defines a central bore having a labyrinth seal diameter, a frusto-conical body extends between the radially inner portion of the housing pilot and the inner rim, and a ratio of a housing pilot thickness to the labyrinth seal diameter is between 0.08 and 0.14, a ratio of the housing pilot thickness to the turbine housing pilot diameter is between 0.0101 and 0.0177, and a ratio of the housing pilot thickness to the compressor housing pilot diameter is between 0.0102 and 0.0178.

10. The method according to claim 9 , wherein a ratio of the turbine housing pilot diameter to the labyrinth seal diameter is between 4.006 and 4.014.

11. The method according to claim 9 , wherein a ratio of the turbine housing pilot diameter to the compressor housing pilot diameter is between 1.001 and 1.003, and a ratio of the labyrinth seal diameter to the compressor housing pilot diameter is between 0.249 and 0.251.

Assignees

• Hamilton Sundstrand Corp

Inventors

• Beers Craig M
• Chrabascz Eric

Classifications

• F05D2220/40

  in turbochargers · CPC title

• F01D11/025 Primary

  Seal clearance control; Floating assembly; Adaptation means to differential thermal dilatations · CPC title

• F01D25/243

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

• F02C7/28

  Arrangement of seals · CPC title

• B64D2013/0648

  with energy recovery means, e.g. using turbines · CPC title