Uncoupled, thermal-compressor, gas-turbine engine

• US 8,037,686 B2
• Filed: 07/03/2007
• Issued: 10/18/2011
• Est. Priority Date: 11/01/2002
• Status: Expired due to Fees

• Current Assignee: George Lasker
• Original Assignee: George Lasker
• Inventors: Lasker, George
• Primary Examiner(s): NGUYEN, HOANG M
• Application Number:
  US11/825,303
• Publication Number:
  US 20110000182A1
• Time in Patent Office: 1,568 Days
• Field of Search: 60677-680, 415/65, 415 68- 69, 415/77
• US Class Current: 60/677
• CPC Class Codes: F02C 1/04 the working fluid being heated indirectly in a fluidised-bed combustor F02C3/205
• CPC Class Codes: F02C 1/05 characterised by the type or source of heat, e.g. using nuclear or solar energy
• CPC Class Codes: F02C 6/00 Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
• CPC Class Codes: F02G 1/04 of closed-cycle type
• CPC Class Codes: F03G 6/064 having a gas turbine cycle, i.e. compressor and gas turbine combination
• CPC Class Codes: F03G 6/068 having other power cycles, e.g. Stirling or transcritical, supercritical cycles; combined with other power sources, e.g. wind, gas or nuclear
• CPC Class Codes: F24S 20/20 Solar heat collectors for receiving concentrated solar energy, e.g. receivers for solar power plants
• CPC Class Codes: F28F 21/04 of ceramic; of concrete; of natural stone
• CPC Class Codes: F28F 3/086 having one or more openings therein forming tubular heat-exchange passages
• CPC Class Codes: Y02E 10/40 Solar thermal energy, e.g. solar towers
• CPC Class Codes: Y02E 10/46 Conversion of thermal power into mechanical power, e.g. Rankine, Stirling or solar thermal engines
• CPC Class Codes: Y02E 20/14 Combined heat and power generation [CHP]
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

The invention is for a continuous-combustion, closed-cycle, gas turbine engine with a regenerator and a displacer. It has embodiments that remove heater and cooler interior volumes during gas compression, which enable it to scale well to very large sizes. Low combustion temperatures insure very low emissions. The displacer levitated by an integral gas bearing and small clearance seal and given oscillatory translational motion by electromagnetic forces operates without surface wear. The turbine blades, subjected only to warm gases, are durable and inexpensive. Thus, this engine has a very long, continuous, maintenance-free service life. This gas turbine engine also operates without back work allowing high efficiency for both low and rated output. Pressurized encapsulation permits use of low-cost ceramics for high temperature components. The invention includes a unique monolithic ceramic heater, a compact high-capacity regenerator and a constant-power gas turbine.

Claims

1. A constant-power, variable-speed gas turbine assembly wherein the assembly converts a portion of an energy of a high pressure gas into mechanical spinning shaft power, maintains near constant power output over a specified turbine rotational speed range, eliminates a need for a separate transmission and with means for magnetically transferring a torque of a turbine contained in a high pressure turbine housing to a region with a different pressure comprising:

(a) a gas nozzle for receiving low-velocity, high-pressure gas and discharging high-velocity, low-pressure gas;

(b) a first turbine blade mounted on a shaft downstream of the nozzle for receiving gas from the nozzle and discharging the gas at a lower velocity thereby generating a first impulse which imparts torque to the shaft;

(c) a stator mounted in the gas turbine assembly downstream from the first turbine blade for changing the direction of gas flow;

(d) a second turbine blade mounted on the shaft for receiving the gas flow from the stator when the gas velocity is greater than a velocity of the second turbine blade and reducing the gas velocity thereof generating a second torque producing impulse and thereby maintaining near constant torque on the shaft;

(e) an internal discharge which receives and discharges gas from the stator when the velocity of the gas is less than the velocity of the second turbine blade;

(f) a high-pressure turbine housing enclosing the gas turbine assembly;

(g) a nonmagnetic and dielectric window in the high pressure turbine housing;

(h) means attached to spinning elements of the turbine for inducing a magnetic field positioned in close proximity to the nonmagnetic and dielectric window; and

(i) means for coupling a magnet field attached to a turbine spinning magnet to a shaft which is external to the high-pressure containment turbine structure.

2. A gas turbine according to claim 1, including means to maintain a near uniform torque output while the intake pressure at a turbine nozzle is fluctuating and further comprising:

(a) means to vary the gas flow rate at the turbine nozzle;

(b) a pressure gauge that measures the pressure upstream of the turbine nozzle; and

(c) a nozzle controller that modulates the nozzle flow.

3. A gas turbine assembly according to claim 2, further comprising:

(a) a planetary reduction gear attached to a turbine output; and

(b) a disk brake system attached to the turbine output thereby enabling the turbine assembly to be utilized in a vehicle-wheel-mountable device.