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Gas-generator augmented expander cycle rocket engine
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 2011 |
| Description | An augmented expander cycle rocket engine includes first and second turbopumps for respectively pumping fuel and oxidizer. A gas-generator receives a first portion of fuel output from the first turbopump and a first portion of oxidizer output from the second turbopump to ignite and discharge heated gas. A heat exchanger close-coupled to the gas-generator receives in a first conduit the discharged heated gas, and transfers heat to an adjacent second conduit carrying fuel exiting the cooling passages of a primary combustion chamber. Heat is transferred to the fuel passing through the cooling passages. The heated fuel enters the second conduit of the heat exchanger to absorb more heat from the first conduit, and then flows to drive a turbine of one or both of the turbopumps. The arrangement prevents the turbopumps exposure to combusted gas that could freeze in the turbomachinery and cause catastrophic failure upon attempted engine restart. |
| File Size | 827339 |
| Page Count | 11 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20110008922 |
| Archival Resource Key | ark:/13960/t4qk2df0t |
| Language | English |
| Publisher Date | 2011-03-08 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Turbine Pumps Gas Generators Thrust Augmentation Upper Stage Rocket Engines Turbomachinery Heat Exchangers Oxidizers Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Patent |
