1. Film Cooling in LF Rockets Erin Schmidt

2. Watch the Heat! Temperatures in LF rocket engines can reach 3600 K Heat transfer rates are on the order of 200 MW/m^2 The basic problem is keeping the nozzle and combustion chamber walls from vaporizing

3. Rocket Engine Heat Transfer There are a few classical approaches to dealing with this problem: Passive cooling -> ablation, radiative cooling, heat sinks Active cooling -> regenerative cooling, film cooling

4. ●LOX-H2 Staged Combustion ●3000 psi Chamber pressure ●2300 kN Thrust Ea. Late 1960’s technology, but remains the current state-of-the-art cryogenic engine. The SSME used film cooling Source: NASA MSFC RS-25 SSME

5. Film Cooling Source: NASA SP-8124, Anon., 1977

6. Ultimately the thing we care about is T w Skipping straight to the solution (similarity solution for B.L. from Schlichting): (T w -T i )/(T m -T i )=1-exp[h 2 αt/k 2 ]erfc[h sqrt(αt)/k] A Conceptual Model

7. All of the assumptions implicit in this result are wrong

8. Big Problems ●Flow has 3D wakes due to injector geometry, lateral flows, separation, and vorticity ●Homogenous reactions within the film ●Turbulent mixing within the film ●Shear mixing at the film interface ●Compressibility-> pressure, density and temperature gradients ●Flow discontinuities (e.g. shock) For any practical rocket engine the simple model has laughably bad predictive power

9. Big Problems Cont. For an isentropic converging- diverging nozzle it is ill-advised to make any of the constant properties assumptions Besides making the governing equations really complex, this adds several levels of coupling between the governing eqns Source: Huzel and Huang, 1967

10. Big Problems Cont. One specific example of coupling is that the reactions in the film are weakly diffusion controlled But binary diffusion coefficients depend on temperature and pressure (which are changing axially in the isentropic flow). Also the reactions couple the energy and species conservation eqns. because the reactions are not isothermal

11. Combustion Products We need to relate T and r. We can do this by balancing enthalpy Hess’s law states that “if a reaction can be carried out as a series of steps, ∆H for the entire reaction is the sum of all ∆H for each step”... ∆H rxn = ∑n p ∆H f,products - ∑n r ∆H f,reactants

12. Combustion Products When a chemical reaction is in equilibrium there are no changes in the molar concentrations of products and reactants with time For a general reaction aA + bB cC + dD there is a constant s.t.K c = [C] c [D] d /[A] a [B] b

13. Combustion Products If K c > 1 equilibrium favors products If K c < 1 equilibrium favors reactants You can also write K c in terms of partial pressures K c =p C c p D d /p A a p B b

14. Equilibrium Constant Method Example: chemical species at equilibrium 2H 2 (g) + O 2 (g) 2H 2 O(g) a) H 2 + ½ O 2 H 2 O b) ½ O 2 + ½ H 2 OH c) ½ H 2 H d) ½ O 2 O

15. Equilibrium Constant Method Equilibrium constants are known functions of temperature! Using the equilibrium constant eqns... a) K p,a = p H2O /p H2 p 1/2 O2 b) K p,b = p OH /p 1/2 H2 p 1/2 O2 c) K p,c = p H /p 1/2 H2 d)K p,d = p O /p 1/2 O2

16. Equilibrium Constant Method Solve for p i, but we only have 4 eqns. in 6 unknowns… Using continuity and the ideal gas law: 2p H2O + p OH + 2p H2 + p H =N H (RT/V) p H2O + p OH + 2p O2 + p O =N O (RT/V) With N H and N O being determined by the concentration gradient

17. Combustion Temperature Now we can solve for p i (and thus n i moles of gas per chemical species)... We can use n i to get the temperature in the reacting B.L.

18. Combustion Temperature Using a simple iterative method: 1.Assume a chamber temperature T ’ at a given pressure 2.Determine equilibrium composition of combustion species at T ’ 3.Calculate: Q available =∆H rxn + ∑ i n i,reactants ∫ Ti Tref C p,i dT

19. Combustion Temperature 4. Calculate: (Use a curve fit equation for C p, usually found in thermodynamic tables, or use lookups from an enthalpy table in lieu of the integral) Q required = -∑ i n i,products ∫ T’ Tref C p dT

20. Combustion Temperature 5. Compare Q available and Q required ; if the difference is greater than your chosen threshold assume a new T ’ 6. Iterate until T converges 7. Use P, T to compute D with Chapman-Engkog or other

21. The point is realistic film-cooling simulations accounting for all these problems are incredibly difficult to do In fact no one has managed to make one yet

22. Std. NASA Correlation Because analytical and numerical approaches leave much to be desired propulsion engineers rely on empirical correlations. This one is the standard for liquid films: where,

23. Reference 1.“Liquid Rocket Engine Self-Cooled Combustion Chambers.” 1977. http://ntrs.nasa.gov/search.jsp?R=19780013268. http://ntrs.nasa.gov/search.jsp?R=19780013268 2.Huang, D. H., and D. K. Huzel. 1971. “Design of Liquid Propellant Rocket Engines Second Edition.” http://ntrs.nasa.gov/search.jsp?R=19710019929.http://ntrs.nasa.gov/search.jsp?R=19710019929 3.Schlichting, H., and K. Gersten. 2000. Boundary-Layer Theory. 8th edition. Berlin; New York: Springer. Thanks! Source: NASA MSFC