Two-spool design for a turboshaft engine with a high-pressure compressor connected to a low-pressure turbine

Patent metadata

Field	Value
Publication number	US-9964033-B2
Application number	US-201214126578-A
Country	US
Kind code	B2
Filing date	Jun 7, 2012
Priority date	Jun 16, 2011
Publication date	May 8, 2018
Grant date	May 8, 2018

Abstract

A turboshaft engine including a low-pressure compressor, a high-pressure compressor, a low-pressure turbine, a high-pressure turbine, and a regulator for regulating a speed of rotation of the low-pressure turbine to a speed that is substantially constant. The low-pressure turbine is coupled by a first shaft to the high-pressure compressor, while the high-pressure turbine is coupled by a second shaft to the low-pressure compressor.

First claim

The invention claimed is:

1. A turboshaft engine comprising:
a low-pressure compressor;
a high-pressure compressor;
a combustion chamber;
a low-pressure turbine;
a high-pressure turbine;
a regulator which regulates an amount of fuel injected into the combustion chamber such that a speed of rotation of the low-pressure turbine is substantially constant;
a first shaft which couples the low-pressure turbine to the high-pressure compressor; and
a second shaft which couples the high-pressure turbine to the low-pressure compressor,
wherein the first shaft passes coaxially inside the second shaft, the first and second shafts defining an axial direction,
wherein the first shaft is longer than the second shaft in the axial direction,
wherein the high-pressure compressor, the low-pressure compressor, the high-pressure turbine, and the low-pressure turbine are arranged in that order along the axial direction, and
wherein the high-pressure compressor is a centrifugal compressor.

2. A turboshaft engine according to claim 1 , forming a helicopter engine.

3. A turboshaft engine according to claim 1 , wherein the low-pressure compressor is an axial compressor.

4. A turboshaft engine according to claim 2 , wherein the first shaft engages with a transmission shaft driving a rotor of the helicopter.

5. A turboshaft engine according to claim 4 , wherein a connection between the first shaft and the transmission shaft is in front of the high-pressure compressor in the axial direction.

Assignees

• Princivalle Remy
• Turbomeca

Inventors

• Princivalle Remy

Classifications

• F05D2220/329

  in helicopters · CPC title

• F02C3/107 Primary

  with two or more rotors connected by power transmission · CPC title

• F02C3/00 Primary

  Gas-turbine plants characterised by the use of combustion products as the working fluid (generated by intermittent combustion F02C5/00) · CPC title