Mid-turbine frame buffer system

Patent metadata

Field	Value
Publication number	US-9382844-B2
Application number	US-201313879471-A
Country	US
Kind code	B2
Filing date	Jan 7, 2013
Priority date	Jan 31, 2012
Publication date	Jul 5, 2016
Grant date	Jul 5, 2016

Abstract

A mid-turbine frame buffer system for a gas turbine engine includes a mid-turbine frame that supports a shaft by a bearing. An air compartment and a bearing compartment are arranged radially inward of the mid-turbine frame. The bearing compartment is arranged within the air compartment and includes first and second contact seals arranged on either side of the bearing. The air compartment includes multiple air seals. A high pressure compressor is fluidly connected to the air compartment and is configured to provide high pressure air to the air compartment. A method of providing pressurized air to a buffer system includes sealing a bearing compartment with contact seals, surrounding the bearing compartment with an air compartment, and supplying high pressure air to the air compartment.

First claim

What is claimed is:

1. A method of providing pressurized air to a buffer system for a gas turbine engine with an outer shaft arranged about an inner shaft, a high pressure compressor mounted to the outer shaft, and a low pressure compressor mounted to the inner shaft, the method comprising steps of:
sealing a bearing compartment comprising a plurality of bearings supporting the outer shaft, with two or more seals; coupling one seal of the two or more seals to the outer shaft and another seal of the two or more seals to the inner shaft;
surrounding the bearing compartment with an air compartment, wherein the bearing compartment is provided between low and high pressure turbines respectively mounted to the inner and outer shafts; and
supplying pressurized air from the high pressure compressor to the air compartment.

2. The method according to claim 1 , wherein the two or more seals comprise contact seals that include a carbon material.

3. The method according to claim 1 , wherein the two or more seals comprise contact seals and two or more air seals, and wherein at least one of the air seals is at least one of a labyrinth seal and a brush seal.

4. The method according to claim 1 , comprising a step of providing a mid-turbine frame supporting the outer shaft by the plurality of bearings, and surrounding the bearing compartment with the air compartment includes the air compartment and the bearing compartment arranged radially inward of the mid-turbine frame, the bearing compartment including a seal assembly provided adjacent the bearing and separating the bearing compartment from the air compartment, the air compartment including two or more air seals, and the applying step includes an air source fluidly connected to the air compartment and configured to provide pressurized air to the seal assembly in the air compartment to buffer the bearing compartment.

5. The method according to claim 4 , wherein at least one bearing of the plurality of bearings is a roller bearing.

6. The method according to claim 4 , wherein the step of providing the mid-turbine frame includes the high and low pressure turbines respectively mounted to the outer and inner shafts, the mid-turbine frame arranged axially between the high and low pressure turbines.

7. The method according to claim 4 , wherein the step of providing the mid-turbine frame includes a lubrication pump fluidly connected to the bearing compartment by a scavenge line.

8. The method according to claim 1 , wherein the two or more seals comprises first and second contact seals, wherein each of the first and second contact seals has first and second members in engagement with one another, and wherein at least one of the first and second members is constructed from a carbon material.

9. The method according to claim 8 , wherein the two or more seals include at least one of a labyrinth seal and a brush seal.

10. The method according to claim 1 , comprising a fan interconnected to the inner shaft via a geared architecture.

Assignees

• United Technologies Corp

Inventors

• Muldoon Marc J
• Reinhardt Gregory E

Classifications

• F02C7/06 Primary

  Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M) · CPC title

• F02C3/10

  with another turbine driving an output shaft but not driving the compressor · CPC title

• F01D11/005

  Sealing means between non relatively rotating elements · CPC title

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title

• F02C7/20 Primary

  Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title