Aerospace Propulsion Assignment 9 — Fuel/Air Burning in Combustor Chambers


B. Parent • AME425 Aerospace Propulsion

Aerospace Propulsion Assignment 9 — Fuel/Air Burning in Combustor Chambers

Instructions

Write your solutions in single column format, with one statement following another vertically. Write your solutions neatly so that they are easy to read and verify. Don't write one line with more than two equal signs. Highlight your answers using a box. Solve the problems starting from the Aerospace Propulsion Tables. Do not use any other document to solve the problems.

05.04.14

Problem #1

Consider air and molecular hydrogen (H$_2$) in gaseous form entering the combustor of a ramjet engine.

(a)

Determine the air-fuel ratio on both a mass and a molar basis for complete combustion of hydrogen with the theoretical amount of air (stoichiometric air-fuel ratio).

(b)

At a given moment, the air enters the combustor at a velocity of 200 m/s and a temperature of 800 K, while the hydrogen is injected in the combustor at negligible velocity with a temperature of 298 K and in stoichiometric proportions:

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Complete combustion of the fuel then occurs in the combustor. Knowing that the temperature of the engine exhaust flow is of 600 K, find the velocity of the exhaust flow using an energy balance and enthalpies determined from the heats of formation. Note: the engine exhaust flow has the same composition as the flow exiting the combustor — it consists of the combustion products of air and hydrogen.

07.18.23

Answers

2.5, 36, 2611 m/s.

11.15.23

Due on Tuesday November 24th at 23:59 on the D2L.

11.12.26

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