Ericsson cycle turbine engine

Patent metadata

Field	Value
Publication number	US-11530644-B1
Application number	US-202117536259-A
Country	US
Kind code	B1
Filing date	Nov 29, 2021
Priority date	Dec 4, 2020
Publication date	Dec 20, 2022
Grant date	Dec 20, 2022

Abstract

An Ericsson cycle turbine engine. The Ericsson cycle turbine may comprise: a centrifugal gas compressor, shaft, at least one heat exchanger, and a reaction turbine. The centrifugal gas compressor may function as a spinning wheel trompe and may be fed with a gas-liquid mixture. The centrifugal gas compressor may separate a gas from the gas-liquid mixture and compress that gas via centrifugal acceleration. The shaft may couple to the downstream end of the centrifugal gas compressor and may have an annular space to permit the compressed gas to travel therein. The heat exchanger may introduce heat to the compressed gas, such that isothermal expansion is approached. The reaction turbine may couple to the downstream end of the shaft and may rotate the shaft when releasing the compressed gas against a plurality of vanes. The liquid may be mercury, oil, or water. The gas may be helium, air, argon, or ammonia.

First claim

What is claimed as new and desired to be protected by Letters Patent is set forth in the appended claims:

1. An Ericsson cycle turbine engine, comprising:
a centrifugal gas compressor being fed with a gas-liquid mixture and configured to separate a gas from said gas-liquid mixture and compress said gas;
a shaft coupled to a downstream end of said centrifugal gas compressor and having an annular space traversing therein, said annular space being configured to permit said compressed gas to travel across said shaft;
a heat exchanger configured to heat said compressed gas; and
a reaction turbine coupled to a downstream end of said shaft and configured to rotate said shaft when releasing said compressed gas against a plurality of vanes;
wherein said shaft is disposed within said heat exchanger and fixedly coupled to said centrifugal gas compressor and said reaction turbine, such that when said reaction turbine rotates, said shaft and said centrifugal gas compressor rotates.

2. The Ericsson cycle turbine engine recited in claim 1 , characterized in that said centrifugal gas compressor comprises:
a rotating container configured to rotate about a central longitudinal axis and having an annular chamber configured to receive said gas-liquid mixture;
a plurality of first fin cavities disposed within said rotating container and extending radially from said annular chamber to a plurality of separation chambers, such that said annular chamber is in fluid communication with said plurality of separation chambers;
a plurality of second fin cavities located within said rotating container and disposed adjacently between said plurality of separation chambers and said plurality of first fin cavities, said plurality of second fin cavities being in fluid communication with said plurality of separation chambers; and
a plurality of compressed gas passages located radially inward from said plurality of separation chambers and in fluid communication between said plurality of separation chambers and said annular space of said shaft, such that said plurality of compressed gas passages are configured to permit transfer of said compressed gas from said plurality of separation chambers into said annular space of said shaft.

3. The Ericsson cycle turbine engine recited in claim 2 , further comprising a plurality of excess fluid passages in fluid communication with said plurality of second tin cavities, said plurality of excess fluid passages being configured to release a liquid without said compressed gas.

4. The Ericsson cycle turbine engine recited in claim 3 , further comprising a plurality of outflow ports in fluid communication with said plurality of excess fluid passages.

5. The Ericsson cycle turbine engine recited in claim 3 , characterized in that said liquid is selected from the group of liquids consisting of: a mercury, an oil, and a water.

6. The Ericsson cycle turbine engine recited in claim 1 , characterized in that said gas is selected from the group of gases consisting of: a helium, an air, an argon, and an ammonia.

7. An Ericsson cycle turbine engine, comprising:
a centrifugal gas compressor being fed with a gas-liquid mixture and configured to separate a gas from said gas-liquid mixture and compress said gas;
a shaft coupled to a downstream end of said centrifugal gas compressor and having an annular space traversing therein, said annular space being configured to permit said compressed gas to travel across said shaft;
a heat exchanger in heat exchange relationship with said shaft and configured to heat said compressed gas, such that isothermal expansion is approached; and
a reaction turbine coupled to a downstream end of said shaft and configured to rotate said shaft when releasing said compressed gas against a plurality of vanes;
wherein said shaft is disposed within said heat exchanger; and
wherein said centrifugal gas compressor, said shaft, and said reaction turbine are centered about a central longitudinal axis and are fixedly coupled to each other, such that when said reaction turbine rotates, said shaft and said centrifugal gas compressor rotates.

8. The Ericsson cycle turbine engine recited in claim 7 , characterized in that said centrifugal gas compressor is a spinning wheel trompe configured to compressed said gas via centrifugal acceleration, said centrifugal gas compressor comprising:
a rotating container configured to rotate about said central longitudinal axis and having an annular chamber configured to receive said gas-liquid mixture;
a plurality of first fin cavities disposed within said rotating container and extending radially from said annular chamber to a plurality of separation chambers, such that said annular chamber is in fluid communication with said plurality of separation chambers;
a plurality of second fin cavities located within said rotating container and disposed adjacently between said plurality of separation chambers and said plurality of first fin cavities, said plurality of second fin cavities being in fluid communication with said plurality of separation chambers; and
a plurality of compressed gas passages located radially inward from said plurality of separation chambers and in fluid communication between said plurality of separation chambers and said annular space of said shaft, such that said plurality of compressed gas passages are configured to permit transfer of said compressed gas from said plurality of separation chambers into said annular space of said shaft.

9. The Ericsson cycle turbine engine recited in claim 8 , further comprising a plurality of excess fluid passages in fluid communication with said plurality of second fin cavities, said plurality of excess fluid passages being configured to release a liquid without said compressed gas.

10. The Ericsson cycle turbine engine recited in claim 9 , further comprising a plurality of outflow ports in fluid communication with said plurality of excess fluid passages.

11. The Ericsson cycle turbine engine recited in claim 9 , characterized in that said liquid is selected from the group of liquids consisting of: a mercury, an oil, and a water.

12. The Ericsson cycle turbine engine recited in claim 7 , characterized in that said gas is selected from the group of gases consisting of: a helium, an air, an argon, and an ammonia.

13. An Ericsson cycle turbine engine, comprising:
a tank having a liquid;
a first heat exchanger configured to heat said liquid;
a gas line configured to introduce gas into said liquid to create a gas-liquid mixture;
a centrifugal gas compressor rotatably coupled to a downstream end of said tank and being fed with said gas-liquid mixture. said centrifugal gas compressor being configured to separate said gas from said gas-liquid mixture and compress said gas by near isothermal compression:
a shaft coupled to a downstream end of said centrifugal gas compressor and having an annular space traversing therein, said annular space being configured to permit said compressed gas to travel across said shaft;
a second heat exchanger in heat exchange relationship with said shaft and configured to heat said compressed gas, such that isothermal expansion is approached; and
a reaction turbine coupled to a downstream end of said shaft and configured to rotate said shaft when releasing said compressed gas against a plurality of vanes;
wherein said shaft is disposed within said second heat exchanger; and
wherein said centrifugal gas compressor, said shaft, and said reaction turbine are centered about a central longitudinal axis and are fixedly coupled to each other, such that when said reaction turbine rotates, said shaft and said centrifugal gas compress

Assignees

• Us Navy

Inventors

• Kemmerer Geoffrey Robert

Classifications

• F02C3/08

  the compressor comprising at least one radial stage (F02C3/10 takes precedence) · CPC title

• F05D2260/22141

  using fins or ribs · CPC title

• F02C7/08 Primary

  Heating air supply before combustion, e.g. by exhaust gases · CPC title

• F05D2210/13

  mixed, e.g. two-phase fluid · CPC title

• F05D2260/10

  Particular cycles · CPC title