Oxygen enhanced pneumatic starting

Patent metadata

Field	Value
Publication number	US-10247104-B2
Application number	US-201615135617-A
Country	US
Kind code	B2
Filing date	Apr 22, 2016
Priority date	Apr 23, 2015
Publication date	Apr 2, 2019
Grant date	Apr 2, 2019

Abstract

A pneumatic starter system for a turbine engine. The pneumatic starter system includes a pneumatic starter and a compressed gas storage unit. The pneumatic starter is configured to cause at least one turbine of the turbine engine to rotate. The compressed gas storage unit is configured to store oxygen rich gas and expel the oxygen rich gas to power the pneumatic starting system to cause the at least one turbine to rotate. The pneumatic starter system also includes a first exhaust path configured to direct at least a first portion of the oxygen rich gas exhausted from the pneumatic starter to a turbine combustion zone of the turbine engine to create an oxygen rich fuel mixture.

First claim

What is claimed is:

1. A turbine engine, comprising:
a pneumatic starter configured to provide starting power to the turbine engine, wherein the pneumatic starter comprises a compressed gas storage tank configured to provide oxygen rich gas to power the pneumatic starter;
a nosecone configured to at least partially house the pneumatic starter;
a combustion zone where fuel for the turbine engine combusts; and
a first exhaust path from the pneumatic starter, wherein the first exhaust path directs at least a first portion of the oxygen rich gas exhausted from the pneumatic starter to the combustion zone to create an oxygen rich fuel mixture in the combustion zone.

2. The turbine engine of claim 1 , wherein the oxygen rich gas is one of substantially pure oxygen gas and oxygen rich gas composed of at least twenty-five percent oxygen.

3. The turbine engine of claim 2 , wherein the pneumatic starter provides starting power to the turbine engine by causing rotation of at least one turbine of the turbine engine.

4. The turbine engine of claim 1 , wherein the nosecone comprises a first void therethrough, and wherein the first exhaust path passes out the nosecone through the first void.

5. The turbine engine of claim 4 , wherein the first portion of the oxygen rich gas exhausted from the pneumatic starter is directed along the first exhaust path to mix with a primary air stream that enters the combustion zone.

6. The turbine engine of claim 4 further comprising:
a second exhaust path from the pneumatic starter motor to the combustion zone, wherein the second exhaust path directs at least a second portion of the oxygen rich gas exhausted from the pneumatic starter to the combustion zone; and
a second void in the nosecone, wherein the second exhaust path passes through the second void to allow the second portion of the oxygen rich gas exhausted from the pneumatic starter to pass therethrough before entering the combustion zone.

7. A pneumatic starter system for a turbine engine, the pneumatic starter system comprising:
a pneumatic starter configured to cause at least one turbine of the turbine engine to rotate;
a nosecone configured to at least partially house the pneumatic starter;
a compressed gas storage unit configured to:
store oxygen rich gas; and
expel the oxygen rich gas to power the pneumatic starter system to cause the at least one turbine to rotate;

wherein the pneumatic starter system further comprises a first exhaust path configured to direct at least a first portion of the oxygen rich gas exhausted from the pneumatic starter to a turbine combustion zone of the turbine engine to create an oxygen rich fuel mixture.

8. The pneumatic starter system of claim 7 , wherein at least the first portion of the oxygen rich gas exhausted from the pneumatic starter is one of one of substantially pure oxygen gas and oxygen rich gas composed of at least twenty-five percent oxygen.

9. The pneumatic starter system of claim 8 , wherein the first exhaust path passes through the nosecone of the turbine engine such that the at least first portion of the oxygen rich gas exhausted from the pneumatic starter exits the nosecone prior to entering the turbine combustion zone.

10. The pneumatic starter system of claim 9 , further comprising a second exhaust path configured to direct at least a second portion of the oxygen rich gas exhausted from the pneumatic starter to the turbine combustion zone.

11. The pneumatic starter system of claim 10 , wherein the turbine engine provides power to one of an airplane and a missile.

12. A method comprising:
starting a gas turbine engine via a pneumatic starter at least partially housed in a nosecone of the gas turbine engine and powered by oxygen rich gas;
exhausting at least a first portion of the oxygen rich gas from the pneumatic starter to a combustion zone of the gas turbine engine to create an oxygen rich fuel mixture; and
igniting the oxygen rich fuel mixture in the combustion zone;
wherein the nosecone is located along an axis of the gas turbine engine and at an air intake of the gas turbine engine, and has a cone shape oriented with the tip to the base in the direction of the air intake.

13. The method of claim 12 , wherein the oxygen rich gas is one of (i) substantially pure oxygen gas and (ii) oxygen rich gas having at least twenty-five percent oxygen.

14. The method of claim 13 , wherein combustion of the oxygen rich fuel mixture in the combustion zone causes a turbine of the turbine engine to continue to rotate.

15. The method of claim 13 , wherein the exhausting at least the first portion of the oxygen rich gas from the pneumatic starter to the combustion zone comprises exhausting at least the first portion of the oxygen rich gas from the pneumatic starter housed outside the nosecone.

16. The method of claim 13 , wherein the turbine engine is coupled to one of an airplane and a missile, and wherein starting the turbine engine via the pneumatic starter occurs while the one of the airplane and the missile is in flight.

17. The method of claim 12 , wherein exhausting at least the first portion of the oxygen rich gas from the pneumatic starter to the combustion zone comprises exhausting the oxygen rich gas out at least one hole in the nosecone.

Assignees

• Rolls Royce Nam Tech Inc

Inventors

• Eifert Andrew J

Classifications

• Y02E20/344

  Cross-Sectional Technologies · mapped topic

• F23R3/286

  having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title

• F05D2260/85

  Starting · CPC title

• F02C7/27 Primary

  Fluid drives (turbine starters F02C7/277) · CPC title

• F23R3/04

  Air inlet arrangements · CPC title