Gas turbine engine with differential gearbox

Patent metadata

Field	Value
Publication number	US-11041444-B2
Application number	US-201816179252-A
Country	US
Kind code	B2
Filing date	Nov 2, 2018
Priority date	Nov 2, 2018
Publication date	Jun 22, 2021
Grant date	Jun 22, 2021

Abstract

A gas turbine engine system includes a boost compressor configured to compress air; a combustor in which the compressed air is mixed with fuel and ignited to generate a stream of combustion gases; and a turbine configured to extract energy from the combustion gases, the turbine being drivingly coupled to the boost compressor and to an output shaft via a differential gearbox configured to apportion an input torque from the turbine between a first output torque applied to the output shaft and a second output torque applied to the boost compressor.

First claim

What is claimed is:

1. A gas turbine engine system, comprising:
a boost compressor configured to compress air;
a high pressure compressor configured to receive compressed air from the boost compressor and further compress the compressed air, the high pressure compressor separately rotatable from the boost compressor;
a combustor in which the compressed air further compressed by the high pressure compressor is mixed with fuel and ignited to generate a stream of combustion gases; and
a turbine configured to extract energy from the combustion gases, the turbine being drivingly coupled to the boost compressor and to an output shaft via a differential gearbox configured to apportion an input torque from the turbine between a first output torque applied to the output shaft and a second output torque applied to the boost compressor,
wherein the differential gearbox comprises a first epicyclic gear set having a first sun gear rotatable about a first axis, a first ring gear rotatable about the first axis, one or more first planet gears, and a first carrier rotatable about the first axis; and the system further comprises:
a second epicyclic gear set having a second sun gear rotatable about a second axis, a second ring gear rotatable about the second axis, one or more second planet gears, and a second carrier rotatable about the second axis; and
a third epicyclic gear set having a third sun gear rotatable about a third axis, a third ring gear rotatable about the third axis, one or more third planet gears, and a third carrier; wherein:
the first sun gear is drivingly coupled to the boost compressor, the first ring gear is fixed, the first carrier ring is drivingly coupled to the second ring gear,
the second sun gear is drivingly coupled to the turbine, the second carrier is drivingly coupled to the third ring gear,
the third sun gear is drivingly coupled to the output shaft, and the third carrier is fixed.

2. The system of claim 1 , wherein the first output torque is different from the second output torque.

3. The system of claim 1 , wherein a rotational speed ratio between the output shaft and the turbine is different from a rotational speed ratio between the boost compressor and the turbine.

4. The system of claim 1 , wherein the output shaft is drivingly coupled to a load compressor, configured to generate compressed air for an environmental control system of an aircraft, and an electric generator.

5. The system of claim 1 , further comprising:
a load compressor drivingly coupled to the output shaft and configured to generate compressed air for an environmental control system of an aircraft; and
a conduit establishing fluid communication between the load compressor and an injection location in a gas path of the gas turbine engine to direct at least some of the compressed air generated by the load compressor to the injection location, the injection location being upstream of the turbine of the gas turbine engine.

6. The system of claim 4 , further comprising a recuperator configured to facilitate heat transfer from exhaust gas from the gas turbine engine to compressed air generated by the load compressor before injecting the compressed air generated by the load compressor in the gas path of the gas turbine engine.

7. The system of claim 1 , wherein the output shaft is drivingly coupled to a propeller via a reduction gearbox.

8. The system of claim 1 , wherein the first epicyclic gear seat is a first reduction gearbox.

9. The system ci claim 8 , wherein the third epicyclic gear set is a second reduction gearbox.

10. The system of claim 1 , wherein the differential gearbox includes a compound epicyclic gear set.

Assignees

• Pratt & Whitney Canada

Inventors

• Redford Tim
• Menheere David H
• Chiappetta Santo
• Van Den Ende Daniel

Classifications

• F02C7/10

  by means of regenerative heat-exchangers · CPC title

• F02C6/08

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

• F02C3/06

  the compressor comprising only axial stages (F02C3/10 takes precedence) · CPC title

• F02C7/32 Primary

  Arrangement, mounting, or driving, of auxiliaries · CPC title

• F02C9/18

  by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} · CPC title