AE6450 Rocket PropulsionRocket Thermochemistry-1Copyright © 2004,2006 by Jerry M. Seitzman. All rights reserved.•Peformadiabatic flame temperaturecalculation with full equilibrium products– pressure = chamber pressure– total enthalpy unchangedCombustor CalculationsAE6450 Rocket PropulsionRocket Thermochemistry-2Copyright © 2004,2006 by Jerry M. Seitzman. All rights reserved.Example Method – GaseqTad()()428.0322.022=××=HOmmMWproductsγγγγproductsAE6450 Rocket PropulsionRocket Thermochemistry-3Copyright © 2004,2006 by Jerry M. Seitzman. All rights reserved.• Constant γ is a very poor assumption for high temperature rocket product gases– can’t use p/po=(T/To)γ/γ-1– even worse assumptionif gas is reacting• Can still calculate isentropicnozzle expansion for two cases– flow stays in equilibriumthrough nozzle (shifting equil.)– flow is frozen - compositioncan not change– find h (and thusu) that matches given p and sIsentropic Expansionhspep2p*pep2p*AE6450 Rocket PropulsionRocket Thermochemistry-4Copyright © 2004,2006 by Jerry M. Seitzman. All rights reserved.Example Method – GaseqWant to examine expansion of productsAE6450 Rocket PropulsionRocket Thermochemistry-5Copyright © 2004,2006 by Jerry M. Seitzman. All rights reserved.Example – Frozen Chemistry•Set pefor nozzle expansionTeMWeγγγγehehoAE6450 Rocket PropulsionRocket Thermochemistry-6Copyright © 2004,2006 by Jerry M. Seitzman. All rights reserved.Example – Shifting EquilibriumMWeγγγγeTe•Exit