Vladimir V Balepin

6619031, Sep 16, 2003

Apr 25, 2001

09/842535

Vladimir V. Balepin - Butte MT, 59710

F02K 500

60246

A multi-mode multi-propellant rocket engine capable of operating in a plurality of selected modes. Propellant components may include liquid hydrogen, liquid hydrocarbon, liquid oxygen, liquid fluorine, and liquid air. The liquid oxygen and the liquid air are stored in separate tanks are mixed in a dedicated mixer prior to their injection into the combustion chamber.

6769242, Aug 3, 2004

Nov 12, 2002

10/292558

Vladimir V. Balepin - Butte MT

MSE Technology Applications, Inc. - Butte MT

B63H 1100

60204, 60257, 60266

The invention is a coolant system for a rocket engine. The rocket engine includes an injector, a fuel supply, an oxidizer supply, a pump for feeding fuel from the fuel supply to the injector, a pump for feeding oxidizer from the oxidizer supply to the injector, a combustor, and a nozzle, the combustor and nozzle forming a combustor and nozzle assembly. The coolant system includes a cooling jacket surrounding the combustor and nozzle assembly. A coolant fluid is supplied to the combustor jacket by a coolant pump that circulates the coolant fluid through the jacket. The coolant fluid vaporizes to cool the combustor and nozzle assembly. A turbine is operatively connected to the coolant pump and is driven by the vaporized coolant from the jacket. A heat exchanger transfers heat from the vaporized fluid to fuel or oxidizer from the supply thereof prior to the feeding of the fuel or oxidizer into the injector. The vaporized coolant fluid is condensed in the turbine and heat exchanger for recirculation to the combustor and nozzle assembly jacket.

7963100, Jun 21, 2011

May 25, 2006

11/442677

Robert J. Bakos - Wading River NY, US
Vladimir V. Balepin - Manorville NY, US
Anthony Castrogiovanni - Manorville NY, US
Jason S. Tyll - Blue Point NY, US

Alliant Techsystems Inc. - Minneapolis MN

F02K 7/10
F02K 7/20

60267, 60266, 60730, 60768

A cooling system for a high-speed vehicle may comprise a combustor wall at least partially enclosing a combustor and which is cooled using a coolant circulating in a Brayton cycle. The heated coolant may be expanded in a turbine, transfer heat to a fuel within a heat exchanger, and be compressed by a compressor before returning to the combustor wall. The combustor wall may be capable of withstanding high temperatures, higher than the temperature at which fuel coking may take place. Heat transfer takes place between the coolant and the combustor wall, and between the coolant and the fuel. A method of cooling an engine for a high-speed vehicle is also disclosed.

8381508, Feb 26, 2013

May 28, 2009

12/473383

Vladimir V. Balepin - Manorville NY, US

Alliant Techsystems Inc. - Arlington VA

B63H 11/00

60204, 60266

Closed-cycle rocket engine assemblies including a combustor assembly, a combustor jacket, a turbine, a first pump and a mixing chamber are disclosed. The combustor jacket facilitates the transfer of heat from the combustor assembly into a fluid and the turbine is driven by a heated fluid from the combustor jacket. The mixing chamber may include a first inlet to receive a fluid from the turbine, a second inlet to receive a fluid from a first reactant reservoir, and an outlet to deliver a fluid to the first pump. Additionally, the first pump may be coupled to and powered by the turbine and the first pump may be configured to deliver at least a portion of the fluid from the mixing chamber into the combustion chamber of the combustor assembly. Related methods of operating such rocket engine assemblies are also disclosed.

20130228076, Sep 5, 2013

Aug 30, 2012

13/599709

VLADIMIR BALEPIN - Manorville NY, US
ANTHONY CASTROGIOVANNI - Manorville NY, US
FLORIN GIRLEA - Sea Cliff NY, US
ANDREW ROBERTSON - West Sayville NY, US
PASQUALE SFORZA - Highland Beach FL, US

B01D 45/16

95271, 55447

Disclosed herein are supersonic separation systems that can be used for the removal of COfrom a mixed gas stream. Also disclosed are methods for the separation and subsequent collection of solidified COfrom a gas stream.

62274864, May 8, 2001

May 28, 1999

9/322050

Vladimir Balepin - Butte MT

MSE Technology Applications, INC. - Butte MT

F02M 6700

244 73R

A single-stage earth-to-orbit launch vehicle employs a combination of rocket engines and turbojet engines to propel a device into orbit. The vehicle is driven through a unique set of operating conditions of the engines to conserve oxidizer and optimize acceleration. Cooling effects of fuel used by both types of engines is employed to maintain operating temperature of the turbojet engines within limits of lightweight materials. The rocket engines are used during initial acceleration and then permitted to remain deeply throttled or idle until the vehicle reaches a speed of about Mach 6. The rocket engine, with most of its oxidizer intact, is then used to accelerate the vehicle into orbit.

62024043, Mar 20, 2001

Oct 9, 1998

9/168620

Vladimir Balepin - Butte MT

MSE Technology Applications, Inc. - Butte MT

F02C 330

60204

A turbojet engine has a capability for propelling an air-borne vehicle over an extremely wide range of operating speeds. A vehicle can be propelled from take-off conditions through speeds in excess of Mach 5. The engine is equipped with a cooling fluid injection system which cools intake air at high operating speeds. Cooling of intake air permits continued turbojet engine operation at speeds which produce stagnation air inlet temperature in excess of those which critical compressor components can tolerate. The inlet air entering the compressor is pre-cooled with injected fluid so that its temperature is reduced below the critical operating temperature limits of the critical compressor components.

20180038316, Feb 8, 2018

Aug 2, 2016

15/226765

- Plymouth MN, US
Vladimir V. Balepin - Manorville NY, US

F02K 9/64
F02K 9/52
F02K 9/58
F02K 9/46

A liquid-fueled rocket engine assembly comprises a combustor assembly, a combustor jacket for cooling the combustor assembly using pressurized liquid fuel exiting a fuel pump, a turbine for expanding gaseous fuel exiting the combustor jacket to power the fuel pump and/or an oxidizer pump, a flow control device for directing expanded gaseous fuel exiting the turbine through a first outlet and/or a second outlet, a discharge device for exhausting the expanded gaseous fuel exiting the first outlet, a heat exchanger for cooling the expanded gaseous fuel exiting the second outlet with some of the pressurized liquid fuel exiting the fuel pump, and a mixer for combining cooled fuel exiting the heat exchanger with liquid fuel to form mixed liquid fuel to be directed into the fuel pump. Another liquid-fueled rocket engine assembly and related methods are also described.