Effects of the Main Gas Path Pressure Field on Rim Seal Flows in a Stationary Linear Cascade

Rim seals in the turbine section of gas turbine engines aim to reduce the amount of purge air required to prevent the ingress of hot mainstream gas into the under-platform space. A stationary, linear cascade was designed, built, and benchmarked to study the effect of the interaction between the pressure fields from an upstream vane row and downstream blade row on hot gas ingress for engine-realistic rim seal geometries. The pressure field of the downstream blade row was modeled using a bluff body designed to produce the pressure distortion of a moving blade. Sealing effectiveness data for the baseline seal indicated that there was little to no ingress with a purge rate greater than 1% of the main gas path flow. Adiabatic endwall effectiveness data downstream in the trench between the vane and blade showed a high degree of mixing. Extending the seal feature associated with the vane endwall indicated better sealing than the baseline design. Steady computational predictions were found to overpredict the sealing effectiveness due to underpredicted mixing in the trench.

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Generalized High Speed Simulation of Gas Turbine Engines

Volume 5: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation; General ◽

10.1115/90-gt-270 ◽

1990 ◽

Cited By ~ 5

Author(s):

Nanahisa Sugiyama

Keyword(s):

Real Time ◽

Gas Turbine ◽

Gas Turbines ◽

High Speed ◽

Power Plants ◽

Turbine Engines ◽

Gas Turbine Engines ◽

Jet Engines ◽

Industrial Gas Turbine ◽

High Degree

This paper describes a real-time or faster-than-real-time simulation of gas turbine engines, using an ultra high speed, multi-processor digital computer, designated the AD100. It is shown that the frame time is reduced significantly without any loss of fidelity of a simulation. The simulation program is aimed at a high degree of flexibility to allow changes in engine configuration. This makes it possible to simulate various types of gas turbine engines, including jet engines, gas turbines for vehicles and power plants, in real-time. Some simulation results for an intercooled-reheat type industrial gas turbine are shown.

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Computer Systems: An Aid to the Development of Gas Turbine Engines

Volume 2: Aircraft Engine; Marine; Microturbines and Small Turbomachinery ◽

10.1115/83-gt-110 ◽

1983 ◽

Author(s):

H. Schneider

Keyword(s):

Gas Turbine ◽

Computer Systems ◽

Turbine Engines ◽

Base Line ◽

Gas Turbine Engines ◽

Line System ◽

Turbine Engine ◽

Soft And Hardware ◽

Engine Development ◽

Effectiveness Data

This paper presents a concept as to the stepwise extension of computer-systems application by KHD Luftfahrttechnik’s engineering departments engaged in gas turbine engine development. A base line system is in used today and criteria have been established to expand this into an efficient engineering tool. Discussed are the principle conditions and targets including items such as cost effectiveness, data communications between different departments, programming, personnel training as well as data analysis and requirements for soft and hardware.

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Effects of Hot Streaks on Adiabatic Effectiveness for a Film Cooled Turbine Vane

Volume 3: Turbo Expo 2004 ◽

10.1115/gt2004-54016 ◽

2004 ◽

Cited By ~ 3

Author(s):

Krishnakumar Varadarajan ◽

David G. Bogard

Keyword(s):

Film Cooling ◽

Field Measurements ◽

Suction Side ◽

Experimental Program ◽

Turbine Engines ◽

Gas Turbine Engines ◽

Turbine Vane ◽

Adiabatic Effectiveness ◽

Hot Streak ◽

Effectiveness Data

Turbine guide vanes in gas turbine engines are typically subjected to localized “hot streaks” emanating from the combustor. This experimental program examined how these hot streaks affect the film cooling performance for these vanes. Adiabatic effectiveness tests were conducted on the showerhead and suction side regions of the vane. Particular attention was placed on how to scale that adiabatic effectiveness data obtained with a hot streak to correctly predict the adiabatic effectiveness. Thermal field measurements were made to determine the temperature gradients for the hot streak near the wall. These experiments showed that the effect of the hot streak on the adiabatic effectiveness could be accounted for by using an “adjusted” mainstream temperature equal to the hot streak temperature at the wall of the vane.

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Approaches to the Prevaporized-Premixed Combustor Concept for Gas Turbines

Volume 1B: General ◽

10.1115/75-gt-85 ◽

1975 ◽

Cited By ~ 1

Author(s):

L. J. Spadaccini ◽

E. J. Szetela

Keyword(s):

Gas Turbine ◽

Gas Turbines ◽

Bluff Body ◽

Porous Plate ◽

Operating Conditions ◽

Fuel Oil ◽

Turbine Engines ◽

Gas Turbine Engines ◽

Operational Conditions ◽

Lean Combustion

An experimental investigation was performed to evaluate a combustor concept which is applicable to gas turbine engines and is believed to offer valuable pollution control advantages relative to the conventional liquid-fuel-spray approach. It involves fuel prevaporization, premixing and lean combustion and may be applied to the design of combustors for aircraft, industrial or automotive powerplants. Two types of bluff-body flameholders, viz. porous-plate and drilled-plate, were evaluated for use as flame stabilizers within the combustor. Tests were conducted under sets of steady-state operational conditions corresponding, respectively, to applications in a low-pressure regenerative-cycle and high-pressure nonregenerative-cycle automobile gas turbine engines. The data acquired can be used to design gas turbine combustors having predicted performance characteristics which are better than those required to meet the most stringent automobile emissions regulations of the Federal “Clean Air Act.” Fuel prevaporization can be accomplished either externally, prior to admission into the engine airstream, or internally by the airstream itself. In support of the prevaporization concept, the feasibility of vaporizing No 2 fuel oil in a heat exchanger which is external to the engine was investigated. Tests conducted at representative operating conditions indicated that a deposit of 0.01 0-in. thickness was collected on the vaporizer wall after 50 hr of operation. A much shorter period of cleaning with hot air was sufficient to remove the deposit.

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Non-Axisymmetric Endwall Profiling in a Turbine Rotor Blade

Volume 1: Turbomachinery ◽

10.1115/98-gt-525 ◽

1998 ◽

Cited By ~ 7

Author(s):

J. C. Hartland ◽

D. G. Gregory-Smith ◽

M. G. Rose

Keyword(s):

Rotor Blade ◽

Pressure Field ◽

Substantial Reduction ◽

Three Dimensional ◽

Turbine Rotor ◽

Secondary Flows ◽

Linear Cascade ◽

Turbine Rotor Blade ◽

Blade Row ◽

Edge Location

A non-axisymmetric endwall profile has been designed using CFD with the aim of reducing endwall pressure non-uniformities downstream of a rotor blade. The purpose was to reduce coolant leakage as proposed by Rose (1994). This profile has been manufactured and fitted to the Durham linear cascade. The experimental endwall pressure distribution agrees very well with the CFD predictions giving a substantial reduction in pressure non-uniformity at the equivalent of the platform edge location downstream. Velocity and total pressure measurements have also been made within and downstream of the blade row to investigate the effects of the profile on the cascade secondary flow. Although the experimental results indicate no significant increase in the secondary flows, a small increase in loss is seen. The CFD predicts these trends also but to a smaller extent. This investigation suggests that with three-dimensional endwall design, the pressure field which provides the driving force of secondary flows can be modified without blade redesign.

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Development of a mathematical model to demonstrate the impact on the fan blades of a high dual-circuit turbofan engine

Journal of Physics Conference Series ◽

10.1088/1742-6596/2094/4/042054 ◽

2021 ◽

Vol 2094 (4) ◽

pp. 042054

Author(s):

D S Shavelkin ◽

V A Kaigorodova

Keyword(s):

Mathematical Model ◽

Composite Materials ◽

Strain State ◽

Turbine Engines ◽

Gas Turbine Engines ◽

Foreign Object ◽

Turbofan Engine ◽

Foreign Objects ◽

High Degree ◽

The Impact

Abstract A mathematical model describing the impact of a foreign object (bird) on the fan blades of a turbofan engine with a high degree of dual circuitry was developed. The validation of the calculation studies was evaluated based on the examination on the prototype engine. Considering the increasing application of composite materials in the designs of prospective aviation gas-turbine engines and assuming the importance of the issue related to providing a sufficient level of airworthiness special attention is paid to the modeling and assessment of the condition of composite fan blades. In this connection the developed model allows to investigate the stress-strain state of the blades made of different, including composite materials, of the fan under the influence of foreign objects and birds on them.

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The Development of a Lean-Premixed Trapped Vortex Combustor

Volume 2: Turbo Expo 2003 ◽

10.1115/gt2003-38236 ◽

2003 ◽

Cited By ~ 9

Author(s):

Jonathan Bucher ◽

Ryan G. Edmonds ◽

Robert C. Steele ◽

Donald W. Kendrick ◽

Blake C. Chenevert ◽

...

Keyword(s):

Applied Sciences ◽

Bluff Body ◽

Combustion Efficiency ◽

Turbine Engines ◽

Gas Turbine Engines ◽

Oxides Of Nitrogen ◽

Elevated Pressures ◽

Lean Premixed ◽

Lean Fuel ◽

Trapped Vortex

A lean-premixed trapped vortex combustor (TVC) has been developed and tested. The TVC was fired on methane and tested at the General Applied Sciences Laboratory (GASL). Additionally, for baseline data, a simple bluff body combustor was tested. All testing was performed at elevated pressures and inlet temperatures and at lean fuel-air ratios representative of power generation gas turbine engines. Both bluff body and TVC data showed competitive oxides of nitrogen (NOx) emissions of <25 ppm (corrected to 15% oxygen dry condition), which served as a basis for future optimization. Combustion efficiency was routinely above 99.5%. An optimized version of the TVC incorporating flame stabilizing features displayed promising emissions: NOx/CO/UHC levels were optimized to as low as 9/9/0ppm (corrected to 15% O2 dry), with corresponding combustion efficiency above 99.9%. Because of this configuration’s robust and straightforward design, it has the potential for successful integration into a prototype engine. This paper describes the combustors, their testing and the evaluation of the test results.

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