Pre-regenerated staged-combustion rocket engine

• US 4,589,253 A
• Filed: 04/16/1984
• Issued: 05/20/1986
• Est. Priority Date: 04/16/1984
• Status: Expired due to Term

• Current Assignee: Rockwell International Corporation
• Original Assignee: Rockwell International Corporation
• Inventors: Wagner, William R.
• Primary Examiner(s): NOT, DEFINED
• Assistant Examiner(s): NOT, DEFINED
• Application Number:
  US06/600,851
• Time in Patent Office: 764 Days
• Field of Search: 60/204, 60/257, 60/258, 60/259, 60/260, 60/266, 60/736
• US Class Current: 60/204
• CPC Class Codes: F02K 9/48 driven by a gas turbine fed by propellant combustion gases or fed by vaporized propellants or other gases

Abstract

An improvement in the design of a staged-combustion-cycle rocket engine. The preburner 16 (or preburners) is operated at a higher temperature than that above which turbine blades will be damaged. A heat-exchanger unit 40 through which the output flow of the cooling jacket 18 of the engine is passed is placed inside the preburners 16, or in close proximity to its output flow, so that heat energy is transferred from the output flow of the preburners 16 to the output flow of the cooling jacket 18. This lowers the preburners output flow to a temperature which will not damage turbine blades and raises the cooling-jacket output flow temperature. Since the output flow of the cooling jacket 18 is fed to the low-pressure turbines 22, the increased temperature raises the pressure of the low-pressure turbines 22 so that their output of flow rate is increased and the flow rate to the engine is increased, thereby increasing engine output power and efficiency.

Claims

1. A method for increasing the power and thrust output of a staged-combustion rocket engine, said engine having a preburner which receives a portion of an output flow of fuel from a fuel tank, said preburner having an output flow for providing a source of energy for a high-pressure turbine of a high-pressure turbopump the output flow of said high-pressure turbine combining with the output flow of a low-pressure turbine of a low-pressure turbopump, said low-pressure turbine receiving the output flow of the cooling jacket of an engine combustion chamber, said cooling jacket having received another portion of the flow from said fuel tank, said combined flow from said high-pressure turbine and from said low-pressure turbine providing a propellant supply for the combustion chamber of said rocket engine, comprising the steps of:

operating said preburner at a temperature, which is high enough so that damage to the blades of said high-pressure turbine would ordinarily occur; and

sending said output flow of the cooling jacket through heat-exchange means prior to being received by said low-pressure turbine, said heat-exchange means in heat exchange relationship with said preburner to extract heat energy from said preburner so that the temperature of the flow being received by said low-pressure turbine is raised, thereby allowing said low-pressure turbopump to be operated at a higher pressure to provide a higher flow rate of fuel through said low-pressure turbopump, and the temperature of the output flow of the preburner is lowered to a level which is below that which will damage the blades of said high-pressure turbine.

2. A method as in claim 1, wherein:

said heat exchange means includes a heat donee element located within the preburner in order to raise the temperature of the cooling jacket output flow.

3. A method as in claim 1, wherein:

the output flow of the cooling jacket is fed through a heat donee element and the output flow of the preburner is fed to a heat donor element, the two components being in close proximity so that heat is transferred from the donor element to the donee element to raise the temperature of the flow in the donee element and lower the temperature of the flow in the donor element.

4. In a staged-combustion engine having a fuel flow path and an oxidizer flow path, said fuel flow path being split into a first flow path and a second flow path, said split occurring after the fuel leaves a fuel tank and is pumped by a low-pressure fuel pump of a low-pressure turbopump and a high-pressure fuel pump of a high-pressure turbopump, said first flow path including at least one preburner and a high-pressure turbine of a high-pressure turbopump, the output flow of said preburner for supplying the energy for said high-pressure turbine before the fuel enters an injector and is then finally combusted in a main combustion chamber, and said second flow path including a cooling jacket for the main combustion chamber and a low-pressure turbine of a low-pressure turbompump, the output flow of said cooling jacket providing the input flow for said low-pressure turbine which feeds its output to the injector, the improvement comprising:

heat-exchanging means, in heat exchange relationship with said preburner, having a donee element for accepting the output flow of the cooling jacket prior to said output flow of said cooling jacket being sent to said low-pressure turbine, said preburner providing heat energy to the output flow of the cooling jacket in said donee element, whereby,

the temperature of the output flow of the preburner is lowered to a level which will not damage said high-pressure turbopump and the temperature of the output flow of the cooling jacket is raised so that the pressure at the low-pressure turbine is raised and the flow to the main combustion chamber is increased.

5. The improvement set forth in claim 4, wherein:

said donee element comprises a coil inside said preburner.

6. The improvement set forth in claim 4, wherein:

said heat-exchanging means comprises at least two coils in close proximity, a donor coil which is connected to receive the output flow of said preburner and a donee coil which is connected to receive the output flow of the cooling jacket.

7. The improvement set forth in claim 4, wherein:

said heat-exchanging means comprises at least a donor element and a donee element, said donor element being connected to receive the preburner output flow and said donee element being connected to receive the cooling jacket output flow.