Granted Patent B2

US 12,742,413 · App. 18/224,921 · Granted Sep 22, 2026

Inventors: Andrew E. Breault (Bolton, CT); William K. Ackermann (East Hartford, CT)

Assignee: RTX Corporation

F02C6/08F02C9/18F05D2260/606

Abstract

Claims (49)

1 . A buffer air assembly for an aircraft engine, the buffer air assembly comprising:

a first pressurized air header;

at least one first bearing compartment connected in fluid communication with the first pressurized air header;

a first bleed air source connected in fluid communication with the first pressurized air header by a first bleed check valve, and the first bleed air source is configured to direct first pressurized bleed air to the first pressurized air header through the first bleed check valve;

at least one electric buffer compressor connected in fluid communication with the first pressurized air header by a first buffer compressor check valve;

at least one second bearing compartment connected in fluid communication with a second pressurized air header;

a second bleed air source, different than the first bleed air source, connected in fluid communication with the second pressurized air header, and the second bleed air source is configured to direct second pressurized bleed air to the second pressurized air header; and

a controller connected in signal communication with the at least one electric buffer compressor, and the controller includes a processor in communication with a non-transitory memory storing instructions, which instructions when executed by the processor, cause the processor to:

energize the at least one electric buffer compressor to direct the pressurized buffering air to the first pressurized air header;

measure a pressure of the first pressurized bleed air or a pressure of the second pressurized bleed air;

identify the measured pressure is greater than or equal to a predetermined threshold pressure; and

deenergize the at least one electric buffer compressor in response to the identification of the measured pressure greater than or equal to the predetermined threshold pressure;

wherein the second pressurized air header is connected in fluid communication with the first pressurized air header by the first buffer compressor check valve; and

wherein the first buffer compressor check valve is configured to direct pressurized air from the second pressurized air header to the first pressurized air header.

2 . The buffer air assembly of claim 1 , wherein the at least one electric buffer compressor includes a single electric buffer compressor, the single electric buffer compressor includes an air outlet and an air inlet, the air outlet is connected in fluid communication with the first pressurized air header by the first buffer compressor check valve, and the second bleed air source is connected in fluid communication with the air inlet.

3 . The buffer air assembly of claim 1 , wherein the instructions, when executed by the processor, further cause the processor to:

measure a pressure of the first pressurized bleed air or a pressure of the second pressurized bleed air;

identify the measured pressure is less than or equal to a predetermined threshold pressure; and

energize the electric buffer compressor to direct the pressurized buffering air to the first pressurized air header in response to identification of the measured pressure less than or equal to the predetermined threshold pressure.

4 . The buffer air assembly of claim 1 , wherein

the second bleed air source is connected in fluid communication with the second pressurized air header by a second bleed check valve; and

the second bleed air source is configured to direct second pressurized bleed air to the second pressurized air header through the second bleed check valve.

5 . An engine for an aircraft, the engine comprising:

a low-pressure compressor;

a high-pressure compressor; and

a buffer air assembly including:

a low-pressure header connected to at least one low-pressure bearing compartment and the low-pressure compressor;

a high-pressure header connected to at least one high-pressure bearing compartment and the high-pressure compressor, the high-pressure header is configured to receive a high-pressure bleed air from the high-pressure compressor, and the high-pressure header is in fluid communication with the low-pressure header; and

at least one electric buffer compressor configured to direct pressurized buffering air to the low-pressure header and the high-pressure header, the at least one electric buffer compressor including an air outlet and an air inlet, the air outlet connected in fluid communication with the low-pressure header, and the air inlet connected in fluid communication with an outlet of the low-pressure compressor;

a controller connected in signal communication with the at least one electric buffer compressor, and the controller includes a processor in communication with a non-transitory memory storing instructions, which instructions when executed by the processor, cause the processor to:

control an engine startup sequence for the engine, the engine startup sequence including energizing the at least one electric buffer compressor to direct the pressurized buffering air to the low-pressure header and the high-pressure header, the pressurized buffering air directed to the high-pressure header is from the low-pressure header.

6 . The engine of claim 5 , further comprising:

a first rotational assembly including the high-pressure compressor;

a second rotational assembly including the low-pressure compressor;

at least one high-pressure bearing assembly rotatably supporting the first rotational assembly, and the at least one high-pressure bearing assembly is connected to the high-pressure header; and

at least one low-pressure bearing assembly rotatably supporting the second rotational assembly, and the at least one low-pressure bearing assembly is connected to the low-pressure header.

7 . The buffer air assembly of claim 5 , wherein the at least one electric buffer compressor includes a single electric buffer compressor, and the single electric buffer compressor is configured to direct the pressurized buffer air to both of the low-pressure header and the high-pressure header.

8 . A buffer air assembly for an aircraft engine, the buffer air assembly comprising:

a first pressurized air header;

at least one first bearing compartment connected in fluid communication with the first pressurized air header;

a first bleed air source connected in fluid communication with the first pressurized air header, and the first bleed air source is configured to direct first pressurized bleed air to the first pressurized air header;

a second pressurized air header;

a second pressurized air header bleed air load connected in fluid communication with the second pressurized air header, the second pressurized air header bleed air load including at least one second bearing compartment, at least one bladed rotor and an engine shaft;

a second bleed air source, different than the first bleed air source, connected to and in fluid communication with the second pressurized air header, and the second bleed air source is configured to direct second pressurized bleed air to the first pressurized air header; and

at least one electric buffer compressor configured to direct pressurized buffer air to the first pressurized air header and the second pressurized air header;

wherein the second pressurized air header is connected in fluid communication with the first pressurized air header by an air header check valve; and

wherein the air header check valve is configured to direct pressurized air from the second pressurized air header to the first pressurized air header.

9 . The buffer air assembly of claim 8 , wherein the at least one electric buffer compressor includes a single electric buffer compressor, and the single electric buffer compressor is configured to direct the pressurized buffer air to both of the first pressurized air header and the second pressurized air header.

10 . The buffer air assembly of claim 8 , wherein the first bleed air source is connected in fluid communication with the first pressurized air header by a first bleed check valve.

Assignments (2)

Continuity (1)

References Cited (22)