Back to results
US 12,497,935 B2Granted
Turbo pump device for rocket engines
OwnerTimucin Erbasinventor
Life of this patent
Estimating the term…
Abstract
An example turbo-pump for a rocket is provided. The example turbo-pump includes a turbine. A first chamber, coupled to the turbine, receives oxidizer fluid resulting in the oxidizer fluid leaving the first chamber at a faster rate to a reaction chamber. A select amount of the oxidizer fluid enters the turbine. A second chamber, coupled to the turbine, receives fuel resulting in the fuel leaving the second chamber at a faster rate to the reaction chamber. A select amount of the fuel enters the turbine. A plurality of pipes is positioned around the turbine. The plurality of pipes is configured to distribute cooling fluid around the turbine to lower the kinetic energy of the select amount of the fuel and the oxidizer fluid within the turbine.
Claims22
A turbo-pump for a rocket comprising:
- a turbo-pump casing;
- a turbine within the casing configured to receive an oxidizer fluid and fuel;
- a first chamber within the casing, coupled to the turbine, for receiving the oxidizer fluid, resulting in the oxidizer fluid leaving the first chamber at a faster rate to a reaction chamber, wherein a select amount of the oxidizer fluid enters the turbine;
- a second chamber within the casing, coupled to the turbine, for receiving the fuel, the fuel leaving the second chamber at a faster rate to the reaction chamber, wherein a select amount of the fuel enters the turbine;
- wherein the turbo-pump casing surrounds an intermediate region of a shaft of the turbo-pump between the first chamber and the second chamber;
- a plurality of capillary pipe inlets disposed in the turbo-pump casing surrounding the intermediate region;
- a plurality of capillary pipe outlets disposed in the turbo-pump casing surrounding the intermediate region;
- and
- a plurality of capillary pipes, wherein each capillary pipe of the plurality of capillary pipes extend entirely within the turbo-pump casing surrounding the intermediate region and external to the turbine from a respective capillary pipe inlet to a respective capillary pipe outlet, the plurality of capillary pipes being configured to distribute cooling fluid external to the turbine to prevent a reaction between the select amount of the fuel and the oxidizer fluid within the turbine.
6 more elements
A method for performing operations of a turbo-pump for a rocket, the method comprising:
- providing a turbo-pump casing;
- providing a turbine within the casing configured to receive an oxidizer fluid and a fuel;
- receiving the oxidizer fluid into a first chamber within the casing, the oxidizer fluid leaving the first chamber at a faster rate, wherein a select amount of the oxidizer fluid enters the turbine;
- receiving the fuel into a second chamber within the casing, the fuel leaving the second chamber at a faster rate to a reaction chamber, wherein a select amount of the fuel enters the turbine;
- and
- wherein the turbo-pump casing surrounds an intermediate region of a shaft of the turbo-pump between the first chamber and the second chamber;
- positioning a plurality of capillary pipe inlets disposed in the turbo-pump casing surrounding the intermediate region;
- positioning a plurality of capillary pipe outlets disposed in the turbo-pump casing surrounding the intermediate region;
- and
- positioning a plurality of capillary pipes within the turbo-pump casing and external to the turbine such that each capillary pipe of the plurality of capillary pipes extend entirely within the turbo-pump casing surrounding the intermediate region from a respective capillary pipe inlet to a respective capillary pipe outlet, the plurality of capillary pipes being configured to distribute cooling fluid external to the turbine to prevent a reaction between the select amount of the fuel and the oxidizer fluid within the turbine.
7 more elements
A turbo-pump for a rocket comprising:
- a turbo-pump casing;
- a turbine within the casing configured to receive an oxidizer fluid and a fuel;
- a first chamber within the casing, coupled to the turbine, for receiving oxidizer fluid, the oxidizer fluid leaving the first chamber at a faster rate to a reaction chamber, wherein a select amount of the oxidizer fluid enters the turbine;
- a second chamber within the casing, coupled to the turbine, for receiving fuel, the fuel leaving the second chamber at a faster rate to the reaction chamber, wherein a select amount of the fuel enters the turbine;
- wherein the turbo-pump casing surrounds an intermediate region of a shaft of the turbo-pump between the first chamber and the second chamber;
- a plurality of capillary pipe inlets disposed in the turbo-pump casing surrounding the intermediate region;
- a plurality of capillary pipe outlets disposed in the turbo-pump casing surrounding the intermediate region;
- and
- a plurality of capillary pipes, wherein each capillary pipe of the plurality of capillary pipes extend entirely within the turbo-pump casing surrounding the intermediate region and external to the turbine from a respective capillary pipe inlet to a respective capillary pipe outlet, the plurality of capillary pipes being configured to distribute cooling fluid external to the turbine to prevent a reaction between the select amount of the fuel and the oxidizer fluid within the turbine;
- and
- at least one outlet coupled to the turbine, the at least one outlet configured to allow a certain amount of the fuel and the oxidizer fluid within the turbine to pass thru the at least one outlet to prevent dangerous pressure imbalances in the turbine.
8 more elements
Dependencies are inferred from the claim text.