Apparatus and process for converting an aero gas turbine engine into an industrial gas turbine engine for electric power production

Patent metadata

Field	Value
Publication number	US-10151211-B2
Application number	US-201514854119-A
Country	US
Kind code	B2
Filing date	Sep 15, 2015
Priority date	Jan 10, 2015
Publication date	Dec 11, 2018
Grant date	Dec 11, 2018

Abstract

An apparatus and a process for converting a twin spool aero gas turbine engine to an industrial gas turbine engine, where the fan of the aero engine is removed and replaced with an electric generator, a power turbine is added that drives a low pressure compressor that is removed from the aero engine, variable guide vanes are positioned between the high pressure turbine and the power turbine, and a low pressure compressed air line is connected between the outlet of the low pressure compressor and an inlet to the high pressure compressor, where a hot gas flow produced in the combustor first flows through the high pressure turbine, then through the low pressure turbine, and then through the power turbine.

First claim

We claim the following:

1. Process of converting a twin spool aero gas turbine engine having an outer spool and an inner spool with a fan into an industrial gas turbine engine that drives an electric generator comprising the steps of:
removing the fan from the twin spool aero gas turbine engine;
removing a first low pressure compressor from the inner spool of the twin spool aero gas turbine engine;
connecting the inner spool to the electric generator;
placing a power turbine downstream from a low pressure turbine such that an exhaust from the low pressure turbine drives the power turbine;
connecting a second low pressure compressor to the power turbine at an aft end of the industrial gas turbine engine such that the power turbine drives the second low pressure compressor to produce low pressure compressed air; and,
passing the low pressure compressed air from the second low pressure compressor into a high pressure compressor of the outer spool;
wherein compressed air from the high pressure compressor passes into a combustor to produce a hot gas stream that flows through the high pressure turbine to the low pressure turbine to drive the electric generator, the exhaust from the low pressure turbine flows through the power turbine that drives the second low pressure compressor, and the low pressure compressed air from the second low pressure compressor flows into the high pressure compressor.

2. The process of converting the twin spool aero gas turbine engine into the industrial gas turbine engine of claim 1 , and further comprising the step of:
placing a row of turbine variable guide vanes at an inlet to the power turbine.

3. The process of converting the twin spool aero gas turbine engine into the industrial gas turbine engine of claim 1 , and further comprising the step of:
reusing the first low pressure compressor of the twin spool aero engine as the second low pressure compressor that is driven by the power turbine in the industrial engine.

4. The process of converting the twin spool aero gas turbine engine into the industrial gas turbine engine of claim 1 , and further comprising the step of:
placing a row of compressor variable inlet guide vanes at an inlet to the second low pressure compressor.

5. An industrial gas turbine engine converted from a twin spool aero gas turbine engine with a fan comprising:
a low spool shaft with a first low pressure turbine directly connected at one end and an electric generator connected at an opposite end, wherein the opposite end is a forward end of the industrial gas turbine engine and a low pressure compressor is removed from the low spool shaft;
a high spool shaft rotatable over the low spool shaft with a high pressure compressor connected to a high pressure turbine;
a combustor connected between the high pressure compressor and the high pressure turbine;
a second low pressure turbine located downstream from the first low pressure turbine such that hot gas exhaust from the first low pressure turbine drives the second low pressure turbine;
wherein the low pressure compressor is located at an aft end of the industrial gas turbine engine and air flows from the low pressure compressor to the high pressure compressor at the forward end of the industrial gas turbine engine through a compressed air line connecting an outlet of the low pressure compressor to an inlet of the high pressure compressor to the combustor to the high pressure turbine to the first low pressure turbine to the second low pressure turbine,
the low pressure compressor driven by the second low pressure turbine; and,
a row of turbine variable guide vanes located between the first low pressure turbine and the second low pressure turbine.

6. The industrial gas turbine engine converted from the twin spool aero gas turbine engine with the fan of claim 5 , and further comprising: all of the compressors and all of the turbines are axial flow devices.

7. The industrial gas turbine engine converted from the twin spool aero gas turbine engine with the fan of claim 5 , and further comprising:
a hot gas flow produced in the combustor passes through the high pressure turbine first, then the first first low pressure turbine, and then through the second low pressure turbine.

8. The industrial gas turbine engine converted from the twin spool aero gas turbine engine with the fan of claim 5 , and further comprising:
the low pressure compressor of the industrial engine is the low pressure compressor of the twin spool aero engine; and,
a row of compressor variable inlet guide vanes at an inlet to the low pressure compressor.

9. An industrial gas turbine engine converted from a twin spool turbofan aero gas turbine engine comprising:
a low spool shaft with a first low pressure turbine directly connected at one end and an electric generator connected at an opposite end, wherein the opposite end is a forward end of the industrial gas turbine engine and a first low pressure compressor is removed from the low spool shaft;
a high spool shaft rotatable over the low spool shaft with a high pressure compressor connected to a high pressure turbine;
a combustor connected between the high pressure compressor and the high pressure turbine;
a second low pressure turbine located downstream from the first low pressure turbine such that hot gas exhaust from the first low pressure turbine drives the second low pressure turbine with the low pressure compressor driven by the second low pressure turbine;
a second low pressure compressor driven by the second low pressure turbine; and,
a row of turbine variable guide vanes located between the first low pressure turbine and the second low pressure turbine;
wherein the second low pressure turbine is located at an aft end of the industrial gas turbine engine and air flows from the second low pressure compressor to the high pressure compressor at the forward end of the industrial gas turbine engine through a compressed air line connecting an outlet of the second low pressure compressor to an inlet of the high pressure compressor to the combustor to the high pressure turbine to the first low pressure turbine to the second low pressure turbine.

10. The industrial gas turbine engine converted from the twin spool turbofan aero gas turbine engine of claim 9 , and further comprising:
all of the compressors and all of the turbines are axial flow devices.

11. The industrial gas turbine engine converted from the twin spool turbofan aero gas turbine engine of claim 9 , and further comprising:
a hot gas flow produced in the combustor passes through the high pressure turbine first, then through the first low pressure turbine, and then through the second low pressure turbine.

12. The industrial gas turbine engine converted from the twin spool turbofan aero gas turbine engine of claim 9 , and further comprising:
the second low pressure compressor of the industrial engine is the first low pressure compressor of the twin spool aero engine; and,
a row of compressor variable inlet guide vanes at an inlet to the second low pressure compressor.

Assignees

• Brostmeyer Joseph D
• Jones Russell B
• Florida Turbine Tech Inc

Inventors

• Brostmeyer Joseph D
• Jones Russell B

Classifications

• F01D15/10 Primary

  Adaptations for driving, or combinations with, electric generators · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D1/04

  traversed by the working-fluid substantially axially · CPC title

• F05D2220/76

  an electrical generator · CPC title

• F02C3/10

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