Advanced integrated propulsion system with total optimized cycle for gas turbines

• US 4,858,428 A
• Filed: 04/24/1986
• Issued: 08/22/1989
• Est. Priority Date: 04/24/1986
• Status: Expired due to Term

• Current Assignee: Marius A. Paul
• Original Assignee: Marius A. Paul
• Inventors: Paul, Marius A.
• Primary Examiner(s): NOT, DEFINED
• Application Number:
  US06/855,847
• Time in Patent Office: 1,216 Days
• Field of Search: 60/39.17, 60/39.27, 60/39.29, 60/39.511, 60/39.161, 60/39.23
• US Class Current: 60/39.17
• CPC Class Codes: F02C 3/13 having variable working fluid interconnections between turbines or compressors or stages of different rotors controlling flow ratio between different flows of multi-flow jet-propulsion plant, e.g. ducted fan F02K3/075
• CPC Class Codes: F02C 9/18 by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages F02C3/113 takes precedence

Abstract

A gas turbine system with integrated high and low pressure circuits having a power transmission for extracting work from one of the circuits, the volume of air and fuel to the respective circuits being varied according to the power demand monitored by a microprocessor, wherein the turbine system has a low pressure compressor and a staged high pressure compressor with a combustion chamber and high pressure turbine associated with the high pressure compressor, and, a combustion chamber and a low pressure turbine associated with the low pressure compressor, the low pressure turbine being staged with the high pressure turbine to additionally receive gases expended from the high pressure turbine and a microprocessor to regulate air and gas flows between the compressor and turbine components in the turbine system.

Claims

1. A gas turbine assembly with integrated high and low pressure circuits comprising:

a low pressure air compressor and a high pressure air compressor staged with the low pressure air compressor;

a first high pressure combustion chamber and associated two-stage, high pressure turbine communicating with the high pressure combustion chamber, the two-stage high pressure turbine having a first stage coupled to the high pressure air compressor and a second stage coupled to the low pressure air compressor;

a second low pressure combustion chamber and associated low pressure, power turbine being staged with the high pressure turbine to receive combustion gases expended from the high pressure turbine;

diverting means between the low pressure compressor and the high pressure compressor for diverting compressed air from the low pressure compressor to the low pressure combustion chamber;

a converging chamber between the low pressure combustion chamber and the low pressure, power turbine constructed to receive and combine combustion gases from the low pressure combustion chamber and exhaust gases from the high pressure turbine;

a junction valve between the low pressure combustion chamber and the covering chamber, the valve being regulatable according to power and efficiency requirements of the turbine assembly to vary the flow of compressed air from the low pressure compressor to the low pressure combustion chamber;

transmission means for extracting mechanical output power, wherein the transmission means for extracting mechanical power is connected to the low pressure power turbine and the high pressure turbine drives the compressors; and

,

fuel supply means for supplying fuel to said first and second combustion chambers wherein a fuel and compressed air mixture is combusted and passed through said turbines.

2. The gas turbine assembly of claim 1 wherein the fuel supply means supplies fuel and coolant to the turbines.

3. The gas turbine assembly of claim 1 wherein the fuel supply means is adapted to separately supply different quantities and qualities of fuels to each turbine.

4. The gas turbine assembly of claim 1 wherein the low pressure turbine receives combustion gases from the high pressure turbine mixed with combustion gases from substantially stoichiometric combustion in the low pressure combustion chamber in a predetermined mixture ratio calculated to produce a gas mixture of permissible temperature for inlet to the low pressure turbine.

5. The gas turbine assembly of claim 1 wherein the combustion chambers are annularly arranged around their associated turbines and the turbines have rotor blades at least a portion of which have peripheral tips communicating with the annular combustion chambers and internal blade passages with outlet ports at the blade tips for ejecting blade coolant passed through the blades, directly into the combustion chambers.

6. The gas turbine assembly of claim 5 wherein the coolant is from the group of air, fuel and water.

7. The gas turbine assembly of claim 5 wherein the coolant is a mixture of substances from the group of air, fuel and water.

8. The gas turbine assembly of claim 1 wherein the low pressure turbine ejects exhaust gases and said assembly includes heat recovery means for extracting thermal energy from the exhaust gases.

9. The gas turbine assembly of claim 1 having control means for regulating the compressed air flow and fuel supply to the combustion chambers according to power demand.

10. The gas turbine assembly of claim 9 wherein the control means includes a microprocessor with input and output sensor means.

11. The gas turbine assembly of claim 10 wherein the control means includes servo means with variable guide vanes for the low pressure compressor, variable guide vanes for the high pressure compressor, variable guide vanes for the low pressure turbine and variable guide vanes for the high pressure turbine.

12. The gas turbine assembly of claim 11 wherein the control means automatically operates the servo means for optimum power and efficiency in the operation of the turbine assembly.

13. The gas turbine assembly of claim 1 wherein the low pressure turbine has a gas exhaust chamber with exhaust dividing means for dividing the exhaust gas into two gas streams, and the turbine assembly has further heat exchanger means in association with the low and high pressure compressors for heating compressed air prior to entry into the combustion chambers.

14. The gas turbine assembly of claim 1 wherein the fuel supply means includes a heat exchanger for preheating fuel.