Design of advanced turbopump drive turbines for National Launch System application

Hüber, Frank; Johnson, P. D.; Montesdeoca, X. A.; Rowey, R. J.; Griffin, Lisa W.

doi:10.2514/6.1992-3221

Cited by 6 publications

(2 citation statements)

References 2 publications

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“…An unconventional blade with a 160 • turning angle is introduced into this counter-rotating turbine. Earlier investigation on this blade in the National Launch System project [7,8] indicates that it can improve turbine efficiency and decrease blade number remarkably.…”

Section: Review Of Counter-rotating Turbine For Turbopumpmentioning

confidence: 99%

The Application of Counter‐Rotating Turbine in Rocket Turbopump

Tang

Zhao²,

Xu³

2008

International Journal of Rotating Machinery

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Counter rotating turbine offers advantages on weight, volume, efficiency, and maneuverability relative to the conventional turbine because of its special architecture. Nowadays, it has been a worldwide research emphasis and has been used widely in the aeronautic field, while its application in the astronautic field is seldom investigated. Researches of counter rotating turbine for rocket turbopump are reviewed in this paper. A primary analysis of a vaneless counter rotating-turbine configuration with rotors of different diameters and rotational speeds is presented. This unconventional configuration meets the requirements of turbopump and may benefit the performance and reliability of rocket engines.

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Section: Review Of Counter-rotating Turbine For Turbopumpmentioning

confidence: 99%

The Application of Counter‐Rotating Turbine in Rocket Turbopump

Tang

Zhao²,

Xu³

2008

International Journal of Rotating Machinery

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“…In the last two decades, many studies have been devoted to the investigation of the flow fields and losses of highly loaded turbine cascades [1][2][3][4][5][6][7][8][9][10]. In recent years, much attention has been paid to an ultra-highly loaded turbine cascade with a turning angle of 160 • by National Aeronautics and Space Administration, Japan whether the blade bowing applies to the ultra-highly loaded turbine cascade and, if it does, find the optimal bow angle.…”

Section: Introductionmentioning

confidence: 99%

Flow fields and losses downstream of an ultra-highly loaded turbine cascade with bowed blades

Tan

Zhang

Chen

et al. 2011

Proceedings of the Institution of Mechanical Engineers, Part A:

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For the first time, a systematic experimental investigation on flow fields and losses of an ultra-highly loaded turbine cascade with bowed blades has been conducted. Flow patterns, secondary flow vortices and vectors, losses, and yaw angles at the downstream outlet have been analysed based on the measurements. The results show that the flow fields downstream of the cascade are characterized by a complicated vortex structure including passage vortices (PVs), trailing edge vortices (TVs), and corner vortices (CVs). The high-loss cores at the cascade outlet roughly correspond to the high-vorticity regions. A −20 • bow angle gives the optimal aerodynamic performance under the conditions of this work, but the overall improvement is not significant. Appropriate negative blade bowing weakens the PVs and TVs and prevents the meeting and mixing of the PVs at the midspan, hence improving the flow fields and reducing the overall losses. However, negative blade bowing also increases the flow separation in corner regions, and enhances the CVs and the accumulation of low-energy air flow. This partially counteracts the beneficial effects, making the overall improvement not significant. The pitch-averaged yaw angle at the outlet of the cascade varies dramatically over the whole span. Negative blade bowing can improve the uniformity of the yaw angle distribution at the outlet. On the contrary, positive blade bowing degrades the aerodynamic performance of the cascade.

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Advancement of Turbine Aerodynamic Design Techniques

Griffin

Hüber

1993

Volume 3C: General

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The Consortium for Computational Fluid Dynamics (CFD) Application in Propulsion Technology has been created at NASA/MSFC. Its purpose is to advance the state-of-the-art of CFD technology, to validate CFD codes and models, and to demonstrate the benefits attainable through the application of CFD in component design. Three teams are currently active within the Consortium: (1) the Turbine Technology Team, (2) the Pump Stage Technology Team, and (3) the Combustion Devices Technology Team. The goals, dynamics, and activities of the Turbine Team are the subjects of this paper. The Consortium is managed by NASA. The Turbine Team is co-coordinated by a NASA representative from the CFD area and an industry (Pratt & Whitney) representative from the area of turbine aerodynamic design. Membership of the Turbine Team includes experts in design, analysis, and testing from the government, industry, and academia. Each member brings a unique perspective, expertise, and experience to bear on the team’s goals of improving turbine efficiency and robustness while reducing the amount of developmental testing. To this end, an advanced turbine concept has been developed within the team using CFD as an integral part of the design process. This concept employs unconventionally high turning blades and is predicted to provide cost and performance benefits over traditional designs. This concept will be tested in the MSFC Turbine Airflow Facility to verify the design and to provide a unique set of data for CFD code validation. Currently, the team is developing and analyzing methods to reduce secondary and tip losses to further enhance turbine efficiency. The team has also targeted volute development as an area that could benefit from detailed CFD analysis.

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Design of advanced turbopump drive turbines for National Launch System application

Cited by 6 publications

References 2 publications

The Application of Counter‐Rotating Turbine in Rocket Turbopump

The Application of Counter‐Rotating Turbine in Rocket Turbopump

Flow fields and losses downstream of an ultra-highly loaded turbine cascade with bowed blades

Advancement of Turbine Aerodynamic Design Techniques

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