MODERN AIRCRAFT ENGINE TESTING

1941 ◽  
Author(s):  
W. D. Gove
Keyword(s):  
Aircraft Engine ◽  
Engine Testing

Measurement of Volatile Particulate Matter Emissions From Aircraft Engines Using a Simulated Plume Aging System

2011 ◽  
Author(s):  
Jay Peck ◽  
Michael T. Timko ◽  
Zhenhong Yu ◽  
Hsi-Wu Wong ◽  
Scott C. Herndon ◽  
...  
Keyword(s):  
Particulate Matter ◽  
Aircraft Engine ◽  
Ambient Conditions ◽  
Sampling System ◽  
Engine Exhaust ◽  
Precursor Material ◽  
Particulate Matter Emissions ◽  
Engine Testing ◽  
Volatile Precursors ◽  
The Impact

Aircraft exhaust contains nonvolatile (soot) particulate matter (PM), trace gas pollutants, and volatile PM precursor material. Nonvolatile soot particles are predominantly present at the engine exit plane, but volatile PM precursors form new particles or add mass to the existing ones as the exhaust is diluted and cooled. Accurately characterizing the volatile PM mass, number, and size distribution is challenging due to this evolving nature and the impact of local ambient conditions on the gas-to-particle conversion processes. To accurately and consistently measure the aircraft PM emissions, a dilution and aging sampling system that can condense volatile precursors to particle phase to simulate atmospheric evolution of aircraft engine exhaust has been developed. In this paper, field demonstration of its operation is described. The dilution/aging probe system was tested using both a combustor rig and on-wing CFM56-7 engines. During the combustor rig testing at NASA Glenn Research Center, the dilution/aging probe supported formation of both nucleation/growth mode particles and soot coatings. The results showed that by increasing residence time, the nucleation particles become larger in size, increase in total mass, and decrease in number. During the on-wing CFM56-7 engine testing at Chicago Midway Airport, the dilution/aging probe was able to form soot coatings as well as nucleation mode particles, unlike conventional 1-m probe engine measurements. The number concentration of nucleation particles depended on sample fraction and relative humidity of the dilution air. The performance of the instrument is analyzed and explained using computational microphysics simulations.

Precision Drilling of Ceramic-Coated Components With Abrasive-Waterjets

1993 ◽  
Vol 115 (1) ◽  
pp. 148-154 ◽  
Author(s):  
M. Hashish ◽  
J. Whalen
Keyword(s):  
Small Diameter ◽  
Aircraft Engine ◽  
Hole Drilling ◽  
Hole Quality ◽  
Barrier Coating ◽  
Drilling Parameters ◽  
Abrasive Waterjets ◽  
Engine Testing ◽  
Engine Components ◽  
Accuracy And Repeatability

This paper addresses an experimental investigation on the feasibility of using abrasive-waterjets (AWJs) for the precision drilling of small-diameter holes in advanced aircraft engine components. These components are sprayed with ceramic thermal barrier coating (TBC), and the required holes are typically 0.025 in. in diameter with a drilling angle of 25 deg. The parameters of the AWJ were varied to study their effects on both quantitative and qualitative hole drilling parameters. The unique techniques of assisting the abrasive feed process, ramping the waterjet pressure during drilling, and varying the jet dwell time after piercing were effectively implemented to control hole quality and size. The results of the experiments indicate the accuracy and repeatability of the AWJ technique in meeting the air flow and hole size requirements. Production parts were drilled for prototype engine testing.

Measurement of Volatile Particulate Matter Emissions From Aircraft Engines Using a Simulated Plume Aging System

2012 ◽  
Vol 134 (6) ◽  
Author(s):  
Jay Peck ◽  
Michael T. Timko ◽  
Zhenhong Yu ◽  
Hsi-Wu Wong ◽  
Scott C. Herndon ◽  
...  
Keyword(s):  
Particulate Matter ◽  
Aircraft Engine ◽  
Ambient Conditions ◽  
Sampling System ◽  
Engine Exhaust ◽  
Precursor Material ◽  
Particulate Matter Emissions ◽  
Engine Testing ◽  
Volatile Precursors ◽  
The Impact

Aircraft exhaust contains nonvolatile (soot) particulate matter (PM), trace gas pollutants, and volatile PM precursor material. Nonvolatile soot particles are predominantly present at the engine exit plane, but volatile PM precursors form new particles or add mass to the existing ones as the exhaust is diluted and cooled. Accurately characterizing the volatile PM mass, number, and size distribution is challenging due to this evolving nature and the impact of local ambient conditions on the gas-to-particle conversion processes. To accurately and consistently measure the aircraft PM emissions, a dilution and aging sampling system that can condense volatile precursors to particle phase to simulate the atmospheric evolution of aircraft engine exhaust has been developed. In this paper, a field demonstration of its operation is described. The dilution/aging probe system was tested using both a combustor rig and on-wing CFM56-7 engines. During the combustor rig testing at NASA Glenn Research Center, the dilution/aging probe supported formation of both nucleation/growth mode particles and soot coatings. The results showed that by increasing residence time, the nucleation particles become larger in size, increase in total mass, and decrease in number. During the on-wing CFM56-7 engine testing at Chicago Midway Airport, the dilution/aging probe was able to form soot coatings along with nucleation mode particles, unlike conventional 1-m probe engine measurements. The number concentration of nucleation particles depended on the sample fraction and relative humidity of the dilution air. The performance of the instrument is analyzed and explained using computational microphysics simulations.

Sea Level Performance of a CF-700 Engine Core With Alternative Fuels

2015 ◽  
Author(s):  
Craig R. Davison ◽  
Pervez Canteenwalla ◽  
Jennifer L. Y. Chalmers ◽  
Wajid A. Chishty
Keyword(s):  
Sea Level ◽  
Alternative Fuels ◽  
Engine Performance ◽  
Performance Testing ◽  
Aircraft Engine ◽  
Test Facility ◽  
Engine Fuel ◽  
Subsequent Test ◽  
Energy Independence ◽  
Engine Testing

The use of alternative fuels has the potential to enhance energy independence and reduce environmental impact of air travel. It is important to characterize gas turbine operation using such fuels under controlled conditions before implementing them in flight. The performance of a CF-700 engine core was examined in a sea level test facility. The following fuels were tested and will be reported on: 1. Jet A-1 – baseline fuel 2. 100% unblended Hydroprocessed Esters and Fatty Acids (HEFA) synthetic kerosene fuel with aromatics (SKA) 3. 100% unblended Fischer-Tropsch (FT) synthetic paraffinic kerosene (SPK) 4. Blended 50% HEFA-SPK and 50% Jet A-1 Fuel 2 above is an alternative fuel that can potentially be used without blending with conventional fuel. One purpose of the static engine testing was to determine if this fuel was suitable for use on subsequent test flights in a Dassault Falcon 20 aircraft. Engine performance testing was conducted at various power settings for each fuel. Relevant plots of performance are presented, compared and discussed. Transient tests were also performed including slams and chops. Observations of the effects of the different fuels on the engine fuel system are presented as some alternative fuels have the potential to cause seals to shrink and leaks to occur. The leaks observed are noted as are the steps taken to mitigate the problem.

CFD Driven Analysis of a Multi-Port Pressure Probe for Real Engine Testing

2017 ◽  
Author(s):  
Aude Lahalle ◽  
Fabrizio Fontaneto ◽  
Tony Arts
Keyword(s):  
Flow Field ◽  
Temperature Sensor ◽  
High Performance ◽  
Turbulence Models ◽  
Aircraft Engine ◽  
Pressure Probe ◽  
Global Flow ◽  
Sensor Location ◽  
Flow Topology ◽  
Engine Testing

During the development phase of an aircraft engine, extensive ground and flight instrumentation testing is performed. The performance of the instrumentation is quantified in terms of Recovery Factor (RF). Experimental data only provide measurement at the sensor location, but no information is available for the flow field taking place in and around the probe. The scope of the present paper is to numerically investigate the flow field taking place inside and around a three Kiel heads rake. The study will focus on the description of the flow field and aims at highlighting the mechanisms affecting the RF. Each head has an elliptical casing and contains a pressure sensor (pneumatic pressure tap) and a temperature sensor (thermocouple). Steady-state RANS simulations have been realized for two different Mach numbers (M = 0.30 and M = 0.65), providing a complete mesh and turbulence models sensitivity analysis. The simulated global flow field demonstrated that regardless of the Mach number, the flow topology is very similar in all cases. The Kiel heads investigation highlighted a well guided flow field confirming the sensors’ high performance.

scholarly journals Precision Drilling of Ceramic-Coated Components With Abrasive-Waterjets

1991 ◽  
Author(s):  
M. Hashish ◽  
J. Whalen
Keyword(s):  
Small Diameter ◽  
Aircraft Engine ◽  
Hole Drilling ◽  
Hole Quality ◽  
Barrier Coating ◽  
Drilling Parameters ◽  
Abrasive Waterjets ◽  
Engine Testing ◽  
Engine Components ◽  
Accuracy And Repeatability

This paper addresses an experimental investigation on the feasibility of using abrasive-waterjets (AWJs) for the precision drilling of small-diameter holes in advanced aircraft engine components. These components are sprayed with ceramic thermal barrier coating (TBC), and the required holes are typically 0.025 inch in diameter with a drilling angle of 25°. The parameters of the AWJ were varied to study their effects on both quantitative and qualitative hole drilling parameters. The unique techniques of assisting the abrasive feed process, ramping the waterjet pressure during drilling, and varying the jet dwell time after piercing were effectively implemented to control hole quality and size. The results of the experiments indicate the accuracy and repeatability of the AWJ technique in meeting the air flow and hole size requirements. Production parts were drilled for prototype engine testing.

High-Temperature Instability of A Cr2Nb-Nb(Cr) Microlaminate Composite

1996 ◽  
Vol 54 ◽  
pp. 374-375
Author(s):  
M. Larsen ◽  
R.G. Rowe ◽  
D.W. Skelly
Keyword(s):  
Heat Treatment ◽  
Solid Solution ◽  
High Temperature ◽  
Elevated Temperatures ◽  
Aircraft Engine ◽  
Lattice Parameter ◽  
Microstructural Stability ◽  
Elevated Temperature Strength ◽  
Cross Sectional ◽  
Bcc Structure

Microlaminate composites consisting of alternating layers of a high temperature intermetallic compound for elevated temperature strength and a ductile refractory metal for toughening may have uses in aircraft engine turbines. Microstructural stability at elevated temperatures is a crucial requirement for these composites. A microlaminate composite consisting of alternating layers of Cr2Nb and Nb(Cr) was produced by vapor phase deposition. The stability of the layers at elevated temperatures was investigated by cross-sectional TEM.The as-deposited composite consists of layers of a Nb(Cr) solid solution with a composition in atomic percent of 91% Nb and 9% Cr. It has a bcc structure with highly elongated grains. Alternating with this Nb(Cr) layer is the Cr2Nb layer. However, this layer has deposited as a fine grain Cr(Nb) solid solution with a metastable bcc structure and a lattice parameter about half way between that of pure Nb and pure Cr. The atomic composition of this layer is 60% Cr and 40% Nb. The interface between the layers in the as-deposited condition appears very flat (figure 1). After a two hour, 1200 °C heat treatment, the metastable Cr(Nb) layer transforms to the Cr2Nb phase with the C15 cubic structure. Grain coarsening occurs in the Nb(Cr) layer and the interface between the layers roughen. The roughening of the interface is a prelude to an instability of the interface at higher heat treatment temperatures with perturbations of the Cr2Nb grains penetrating into the Nb(Cr) layer.

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