Dismiss
InnovationQ will be updated on Sunday, Oct. 22, from 10am ET - noon. You may experience brief service interruptions during that time.
Browse Prior Art Database

Aviation Turbo-Pump for Single- and Dual-Fuel Engines

IP.com Disclosure Number: IPCOM000239634D
Publication Date: 2014-Nov-20
Document File: 3 page(s) / 96K

Publishing Venue

The IP.com Prior Art Database

This text was extracted from a PDF file.
This is the abbreviated version, containing approximately 51% of the total text.

Page 01 of 3

Aviation Turbo-Pump for Single- and Dual-Fuel Engines

Background:

    In some known engine systems, cryogenic fuels (e.g., liquid natural gas) or kerosene-type fuels are maintained at low temperatures and low pressures until the fuel is supplied to the engine. For proper engine operation, the pumped fuel is typically maintained in predetermined pressure and temperature ranges. In the case of liquid natural gas (LNG), the fuel is often vaporized from a liquid to a gas. In some known engine systems, electric pumps are used to pump fuel to the engine, but such electric pumps require power to operate. Described herein is a fuel pump that uses little to no electric power and is self-regulating.

    In some known rocket engines, turbo-pumps have been used to provide high-thrust, long- duration operability. Turbo-pumps are recognized in the art of rocket engines for a high power- to-weight ratio and a capability of operation at high speeds. However, turbo-pumps in rocket engines are not self-regulating systems because such turbo-pumps must provide immense thrust to the rocket at a specific time in its flight. In other words, the turbo-pump in some known rocket engine systems is not meant to provide thrust throughout the rocket's flight.

Body:

    Generally, the system described herein provides a turbo-pump design for use in aviation engines than can be self-regulating. FIG. 1 shows a simplified schematic design of one embodiment of the turbo-pump. The illustrated embodiment is placed upstream of the engine and downstream of the fuel tank. In some embodiments, the turbo-pump is formed of metal. In other embodiments, the turbo-pump is formed of a composite material or any other suitable material that enables the turbo-pump to perform as described herein. In various embodiments, the turbo- pump system described herein may be used in many aircraft engine systems, including, but not limited to, turbo-fan, turbo-jet, turbo-prop, open-rotor, and other aircraft engine systems.


Page 02 of 3

FIGURE 1:TURBO-PUMP SCHEMATIC

    In some embodiments, the turbo-pump is part of an expander cycle. Cryogenic fuel (e.g., LNG) is heated and pressurized before it is supplied to the engine of an aircraft. In some embodiments, the cryogenic fuel is heated using a vaporizer, as shown in FIG. 1, to vaporize and pressurize the fuel. In some known systems, the energy given off by the vaporizer (e.g., exhaust) in heating the fuel is merely dissipated into the vaporizer's immediate environment. In the illustrated embodiment, this excess energy is used to power a turbine, which in turn powers the turbo-pump. In some embodiments, the turbo-pump may require another power source (e.g., electric power) during a "warm-up" stage, in which the turbine is not yet spinning at a high enough speed to generate the energy necessary to run the turbo-pump. In some embodiments, the illustrated embodiment is self-regulating during the flight of the aircraft and requires little to no electrical powe...