lecture_28 - 16.512 Rocket Propulsion Prof Manuel...

Info iconThis preview shows pages 1–2. Sign up to view the full content.

View Full Document Right Arrow Icon
16.512, Rocket Propulsion Prof. Manuel Martinez-Sanchez Lecture 28: Mechanical Design of Turbomachinery Integration and Rotordynamics of Turbo Pumps 1. Integration and Mechanical Components As noted before, turbines and pumps are often mounted on a common shaft. If the oxidizer and fuel have similar densities, their respective pumps can also be on one shaft. This is the case in the MK-3 Atlas and Delta II booster turbopump, which, however, has a geared turbine-pump transmission. The Russian RD-170 takes a further integration step by having a single turbine drive both, fuel and oxidizer pump, all on a single shaft. In addition, these pumps feed not a single thrust chamber, but a cluster of four in the case of the Energia vehicle (Fig 4, Lec. 24). Engines using LH fuel require different speeds for the oxidizer and fuel pumps. The first of these engines, the RL-10, had a single-stage oxygen pump on one shaft, gear driven by a second shaft on which were mounted a 2-stage hydrogen pump and the drive turbine. More recent engines (LE-7, SSME) feature separate shafts for the oxygen and fuel, each carrying its own drive turbine.
Background image of page 1

Info iconThis preview has intentionally blurred sections. Sign up to view the full version.

View Full DocumentRight Arrow Icon
Image of page 2
This is the end of the preview. Sign up to access the rest of the document.

This note was uploaded on 11/07/2011 for the course AERO 16.512 taught by Professor Manuelmartinez-sanchez during the Fall '05 term at MIT.

Page1 / 3

lecture_28 - 16.512 Rocket Propulsion Prof Manuel...

This preview shows document pages 1 - 2. Sign up to view the full document.

View Full Document Right Arrow Icon
Ask a homework question - tutors are online