Power turbine system with fuel injector and condensor

Patent metadata

Field	Value
Publication number	US-10844815-B2
Application number	US-201816209209-A
Country	US
Kind code	B2
Filing date	Dec 4, 2018
Priority date	Mar 29, 2016
Publication date	Nov 24, 2020
Grant date	Nov 24, 2020

Abstract

The power turbine system includes two power turbines communicating with an ion transport membrane (ITM) reactor. Heavy liquid fuel is atomized and burned within the reactor to drive the first turbine, with the first turbine producing useful power. Exhaust from the first turbine is recycled back into the reactor. The reactor includes a series of concentric cylindrical ion transport membranes that separate atmospheric and exhaust gases into suitable components for combustion therein, with at least some of the gases being “cracked” to alter their molecular structure for further combustion to power the second turbine. The second turbine drives a compressor to supply air to the reactor. At least one of the ITMs precludes atmospheric nitrogen from the combustion processes, with the resulting exhaust including pure water and carbon dioxide. The carbon dioxide is either recycled into the reactor to facilitate fuel atomization, or compressed for sequestration.

First claim

We claim:

1. A power turbine system with integrated fuel line and condenser, comprising:
a multi-stage ion transport membrane reactor, the multi-stage ion transport membrane reactor having an elongate fuel, evaporation core, a first air delivery passage disposed above the fuel evaporation core, a button cell ion transport membrane disposed between the fuel evaporation core and the first air delivery passage, and a plurality of ion transport membranes spaced from the elongate fuel evaporation core and the first air delivery passage, the membranes defining corresponding working chambers therebetween;
a first power turbine communicating with the reactor;
a second power turbine communicating with the reactor;
an air compressor communicating with the second power turbine and the reactor;
a cylindrical fuel partial conversion chamber disposed concentrically about the fuel evaporation core;
a gaseous nitrogen output chamber disposed concentrically about the first air delivery passage;
a cylindrical fuel complete conversion chamber disposed concentrically about the fuel partial conversion chamber and the gaseous nitrogen output chamber;
a cylindrical first oxygen separation membrane disposed concentrically about the fuel complete conversion chamber;
a cylindrical second air delivery passage disposed about the first oxygen separation membrane;
a cylindrical second oxygen separation membrane disposed concentrically about the second air delivery passage;
a synthetic gas combustion chamber disposed concentrically about the second oxygen separation membrane;
a cylindrical third oxygen separation membrane disposed concentrically about the synthetic gas combustion chamber;
a first turbine exhaust collection and synthetic gas production chamber disposed concentrically about the third oxygen separation membrane; and
a cylindrical second turbine exhaust collection chamber disposed concentrically about the first turbine exhaust collection chamber,
wherein the power turbine system further comprises a fuel line passing through a condenser and connecting to a fuel injector disposed at an upstream end of the elongate fuel evaporation core, wherein the condenser is connected to the second turbine exhaust collection chamber such that an exhaust mixture passes from the second turbine exhaust collection chamber through the condenser in a countercurrent direction to a fuel flow in the fuel line and the exhaust mixture is cooled by the fuel line in the condenser to condense water.

2. The power turbine system according to claim 1 , wherein the ion transport membranes are disposed in a mutually concentric cylindrical array.

3. The power turbine system according to claim 1 , further comprising:
a heavy liquid fuel heater disposed within the reactor, the reactor combusting a heavy liquid fuel therein to produce at least exhaust product, a portion of the at least one exhaust product comprising carbon dioxide; and
a water and carbon dioxide condenser and collector disposed externally to the reactor, the condenser and collector communicating with the reactor, the condenser and collector recycling a first portion of collected carbon dioxide back to the reactor and further delivering a second portion of collected carbon dioxide for sequestration.

4. The power turbine system according to claim 1 , wherein the first turbine exhaust collection and synthetic gas production chamber communicates with the first turbine and the second turbine exhaust collection chamber communicates with the second turbine.

5. The power turbine system according to claim 1 , wherein the first oxygen separation membrane, the second oxygen separation membrane, and the third oxygen separation membrane include ion transport membranes.

6. The power turbine system according to claim 1 , wherein:
the fuel partial conversion chamber is adapted for partial combustion of fuel therein; and
the fuel complete conversion chamber communicates with the fuel partial conversion chamber, the fuel complete conversion chamber being adapted for complete combustion of fuel therein.

7. A method for liquid fuel combustion using the multi-stage ion transport membrane reactor according to claim 1 , comprising the steps of:
introducing liquid fuel into the elongate fuel evaporation core;
introducing compressed atmospheric air into the first air delivery passage;
separating oxygen from the compressed atmospheric air through the button cell ion transport membrane;
introducing the oxygen into the fuel partial conversion chamber through the button cell ion transport membrane;
partially converting fuel flowing m the partial conversion chamber using the oxygen flowing from the button cell ion transport membrane to provide partially converted fuel;
flowing the partially converted fuel into the fuel complete conversion chamber;
introducing compressed atmospheric air into the second air delivery passage;
passing oxygen from the atmospheric air in the second air delivery passage through the first oxygen separation membrane into the fuel complete conversion chamber for complete combustion of fuel flowing therein to provide a first exhaust product comprising carbon dioxide (CO 2 ) and water (H 2 O);
powering the first turbine with the first exhaust product;
flowing the first exhaust product from the first turbine through the first turbine exhaust collection and synthetic gas production chamber to the synthetic gas combustion chamber;
receiving oxygen in the synthetic gas combustion chamber through the second and third oxygen separation membranes to completely combust the first exhaust product in the synthetic gas combustion chamber and produce a second exhaust product; and
driving the second power turbine with the second exhaust product.

Assignees

• Univ King Fahd Pet & Minerals

Inventors

• Nemitallah Medhat A
• Habib Mohamed A

Classifications

• F02C3/24 Primary

  the fuel or oxidant being liquid at standard temperature and pressure · CPC title

• B01D53/22

  by diffusion (manufacturing semi-permeable membranes B01D67/00; form, structure or properties of semi-permeable membranes B01D69/00; material for semi-permeable membranes B01D71/00) · CPC title

• C01B13/0251

  by making use of membranes · CPC title

• B01D53/265

  by refrigeration (condensation) · CPC title

• F02M27/00 Primary

  Apparatus for treating combustion-air, fuel, or fuel-air mixture, by catalysts, electric means, magnetism, rays, sound waves, or the like · CPC title