Injector with Seals

Injector Seals

We machined glands into the injector bottom face which hold copper seals. These seals will prevent hot combustion gases from leaking through the joint between the combustion chamber wall and the bottom face of the injector.

The combustion chamber is test-fitted to a half finished injector. The rocket's propellants will mix and spray out of the six orifices in the injector.

Injector and Combustion Chamber

We’ve begun to make components for the next iteration of the Pyralis engine. As this version will burn ethanol and nitrous oxide at high temperatures, we need to make the components from materials which can take the heat. The picture below shows the combustion chamber wall being fitted to a half-finished injector. Both are made…

The new spike, made of 6061 Aluminum

New Spike!

We made a new nozzle for the cold-flow rocket engine. By comparing the results of cold-flow tests performed on the two spike versions, the team is gaining valuable insights about aerospike nozzle design.

Looking up the nozzle of the Pyralis Cold Flow prototype

Cold Flow Test!

Today the MIT Rocket Team conducted a successful cold flow test of the Pyralis rocket engine prototype. We flowed compressed nitrogen gas at 4.1 MPa (600 psi) pressure through the engine’s nozzle and combustion chamber, generating about 220 N (50 lbs) of thrust force. Over the next weeks,we will continue to test the Cold-Flow prototype…

James and Ryan setting up the Test Stand in the Gas Turbine Lab

Cold Flow Test Setup

We’ve spent the past week putting the finishing touches on the Cold Flow test stand and engine. Yesterday, we moved the test stand into a blast chamber in MIT’s Gas Turbine Lab where we will conduct several Cold Flow tests of the Pyralis prototype next week. Thanks to Jimmy Letendre and Prof. Spakovszky for letting…


Test Stand & Cold-Flow Prototypes

The test stand is finished and ready to be used for the upcoming cold-flow test.                               Connie L, James L, Eric R, and Matt V finished machining and assembling the injector plate and the cage that will enclose the Pyralis engine…

temp scale

Pyralis Thermal Simulation

During firing of the Pyralis engine, heat from the combustion process will flow though the walls of the combustion chamber. The wall consists of of an insulating liner which absorbs heat, surrounded by a structural wall which contains the pressure load of the engine and is protected from intense heat by the insulating liner. The…

Pyralis Design Meeting

We had a design meeting tonight. Major points discussed: – Sensing equipment: for cold flow we need only 4 measurements: tank pressure, engine chamber pressure, engine inlet temperature, and thrust. Assuming adiabatic expansion of gas from the tank, d(p_tank)/dt will give us the mass flow rate out of the tank. Eric recommends that we measure…