On the Multiplicity of Steady Gas Flows Having the Same Streamline Pattern

Munk, Max M; Prim, R. C.

doi:10.1073/pnas.33.5.137

Cited by 122 publications

(51 citation statements)

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“…The augmentation levels of the two curves--representing different ambient temperatures--differ by approximately 2%. It is interesting to note that similar amounts of reduction in the augmentation ratio can take place by (1) decreasing the secondary flow temperature by about 30'R, or (2) increasing the primary nozzle temperature by about 500'R. Supporting this result is Figure 7 [ref. 51, which includes the experimental results of eight different ejectors.…”

Section: Total Thnert Load Cell Measurement Primary-nozzle Ideal Thrusupporting

confidence: 64%

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Use of an approximate similarity principle for the thermal scaling of a full-scale thrust augmenting ejector

Barankiewicz

Perusek

Ibrahim

1992

28th Joint Propulsion Conference and Exhibit

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Full temperature ejector model simulations are expensive, and difficult to implement experimentally. If an appropriate similarity principle could be established, properly chosen performance parameters should be similar for both hot flow and cold flow model tests if the initial Mach numbers and total pressures of the flowfield are held constant. In this investigation, existing ejector data is used to explore the utility of one particular similarity principle --the Munk and Prim similarity principle for isentropic flows. Static performance test data for a full-scale thrust augmenting ejector are analyzed for primary flow temperatures up to 1560'R. At different primary temperatures, exit pressure contours are compared for similarity. A nondimensional flow parameter is then used to eliminate primary nozzle temperature dependence and verify similarity between the hot and cold flow experiments.

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Section: Total Thnert Load Cell Measurement Primary-nozzle Ideal Thrusupporting

confidence: 64%

“…This is an extension of the Munk and Prim Principle [ref. 2] for steady isentropic flows, where the current approach includes the nonisentropic (viscous) effects.…”

mentioning

confidence: 99%

Use of an approximate similarity principle for the thermal scaling of a full-scale thrust augmenting ejector

Barankiewicz

Perusek

Ibrahim

1992

28th Joint Propulsion Conference and Exhibit

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“…Moore & Pullin (1998) discuss several admissible continuations of the incompressible Hill's spherical vortex flow to give solutions of the steady compressible Euler equations. These include the assumption of homethalpic flow in place of the present homentropic flow and the application of a transformation which generates new solutions of the steady Euler equations from a given solution (Munk & Prim 1947). These methods can be applied to the present Stuart vortex flow.…”

Section: Discussionmentioning

confidence: 99%

On steady compressible flows with compact vorticity; the compressible Stuart vortex

2000

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Numerical and analytical solutions to the steady compressible Euler equations corresponding to a compressible analogue of the linear Stuart vortex array are presented. These correspond to a homentropic continuation, to finite Mach number, of the Stuart solution describing a linear vortex array in an incompressible fluid. The appropriate partial differential equations describing the flow correspond to the compressible homentropic Euler equations in two dimensions, with a prescribed vorticity-densitystreamfunction relationship. In order to construct a well-posed problem for this continuation, it was found, unexpectedly, to be necessary to introduce an eigenvalue into the vorticity-density-streamfunction equation. In the Rayleigh-Janzen expansion of solutions in even powers of the free-stream Mach number M ∞ , this eigenvalue is determined by a solvability condition. Accurate numerical solution by both finitedifference and spectral methods are presented for the compressible Stuart vortex, over a range of M ∞ , and of a parameter corresponding to a confined mass-flow rate. These also confirm the nonlinear eigenvalue character of the governing equations. All solution branches followed numerically were found to terminate when the maximum local Mach number just exceeded unity. For one such branch we present evidence for the existence of a very small range of M ∞ over which smooth transonic shock-free flow can occur.

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“…Turbine designers are interested in how the approaching flow field affects the HPT's aerodynamics and cooling performance. Fundamental theories regarding hot streak migration are based on the work of (a) Munk and Prim [10] and (b) Kerrebrock and Mikolajczak [11]. They showed that: (a) in steady flows with constant entropy along each streamline the streamline pattern is not affected by variations of inlet total temperature for an unchanged total pressure distribution; and that (b) hot gas migration through an NGV passage will result in the formation of positive jets in the rotor, i.e., hot gas will preferably accumulate at the blade's pressure side (PS), also known as preferential heating.…”

Section: Introductionmentioning

confidence: 99%

Parameterised Model of 2D Combustor Exit Flow Conditions for High-Pressure Turbine Simulations

Schneider

Schiffer

Lehmann

2017

IJTPP

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An algorithm is presented generating a complete set of inlet boundary conditions for Reynolds-averaged Navier-Stokes computational fluid dynamics (RANS CFD) of high-pressure turbines to investigate their interaction with lean and rich burn combustors. The method shall contribute to understanding the sensitivities of turbine aerothermal performance in a systematic approach. The boundary conditions are based on a set of input parameters controlling velocity, temperature, and turbulence fields. All other quantities are derived from operating conditions and additional modelling assumptions. The algorithm is coupled with a CFD solver by applying the generated profiles as inlet boundary conditions. The successive steps to derive consistent flow profiles are described and results are validated against flow fields extracted from combustor CFD.

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On the Multiplicity of Steady Gas Flows Having the Same Streamline Pattern

Cited by 122 publications

References 0 publications

Use of an approximate similarity principle for the thermal scaling of a full-scale thrust augmenting ejector

Use of an approximate similarity principle for the thermal scaling of a full-scale thrust augmenting ejector

On steady compressible flows with compact vorticity; the compressible Stuart vortex

Parameterised Model of 2D Combustor Exit Flow Conditions for High-Pressure Turbine Simulations

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