公开(公告)号：US20170254296A1

公开(公告)日：2017-09-07

申请号：US15059884

申请日：2016-03-03

Applicant: Daniel Patrick Weldon ,  Kevin Patrick Weldon

Inventor： Daniel Patrick Weldon ,  Kevin Patrick Weldon

IPC: F02K99/00 ,  F02K9/42 ,  F02K9/60 ,  F02K9/97

CPC classification number: F02K9/605 ,  F02K9/425 ,  F02K9/44 ,  F02K9/972

Abstract: According to one contemplated embodiment of the rocket engine invention, water is first pumped from a water tank through a rocket nozzle cooling heat exchanger wherein it is evaporated into said superheated steam. A generator supplies electricity to an electrolyzer that electrolyzes superheated steam into gaseous hydrogen and gaseous oxygen. The gaseous hydrogen and gaseous oxygen is employed for forming an annular curtain of secondary combustion in a divergent rocket engine. The secondary combustion gas surrounds a central thrust of combustion gas produced in an upstream combustion chamber by a primary injection of hydrogen/oxygen supplied from a liquid hydrogen tank and liquid oxygen tank. The rocket liquid hydrogen tank and liquid oxygen tank are pressurized by gaseous hydrogen and gaseous oxygen generated by the electrolyzer.

公开(公告)号：US11181076B2

公开(公告)日：2021-11-23

申请号：US15059884

申请日：2016-03-03

Applicant: Kevin Michael Weldon ,  Daniel Patrick Weldon

Inventor： Daniel Patrick Weldon ,  Kevin Patrick Weldon

IPC: F02K9/42 ,  F02K9/97 ,  F02K9/60 ,  F02K9/44 ,  F02K9/56 ,  F02K9/64 ,  F02K9/82 ,  F02K9/50 ,  F02K9/52 ,  F02K9/48 ,  F02K9/68 ,  F02C9/58 ,  B64G1/40

Abstract: According to one contemplated embodiment of the rocket engine invention, water is first pumped from a water tank through a rocket nozzle cooling heat exchanger wherein it is evaporated into said superheated steam. A generator supplies electricity to an electrolyzer that electrolyzes superheated steam into gaseous hydrogen and gaseous oxygen. The gaseous hydrogen and gaseous oxygen is employed for forming an annular curtain of secondary combustion in a divergent rocket engine. The secondary combustion gas surrounds a central thrust of combustion gas produced in an upstream combustion chamber by a primary injection of hydrogen/oxygen supplied from a liquid hydrogen tank and liquid oxygen tank. The rocket liquid hydrogen tank and liquid oxygen tank are pressurized by gaseous hydrogen and gaseous oxygen generated by the electrolyzer.