Browse Topic: Turboprop engines

Items (84)

Prediction and Estimation of Propeller Drag

11/30/2022

Turboprop aircraft have the capability of reversing thrust to provide extra stopping power during landing. Reverse thrust helps save the wear and tear on the brakes and reduces the landing distance under various conditions. The article explains a methodology to predict the disking drag (reverse thrust) from the Computational Fluid Dynamics (CFD) technique using Blade Element Momentum (BEM) theory and estimation of the same from high-speed taxiing trial (HSTT) and ground roll data for a turboprop aircraft using system identification techniques. One-dimensional kinematic equation was used for modeling the aircraft dynamics, and the error between measured and estimated responses was optimized using the Output Error Optimization Method (OEOM). The estimated propeller drag was matched with CFD predictions to arrive at a relation between the propeller blade pitch angle and throttle position. The present study also investigates the estimation of the braking friction coefficient from the

Nusrath T. K., Khadeeja, Kaliyari, Dushyant, Puttam, Jyothi Kumar, Madhu Babu, K., Arshad Shameem, C., Jaiswal A, Shikhar, Sajjan, Sharanappa V., Venkatesh, T. N., Pashilkar, Abhay A.

Exergetic Investigation of a Turboshaft Helicopter Engine Related to Engine Power

01-13-02-001910/19/2020

Turboshaft engines, one of the classifications of the helicopters, combine the core engine and fan and consume fossil fuels. Emissions, produced by the fossil fuels, cause global warming and environmental pollution, such as ecological, human health. To improve helicopter capability, energy is the first point of improvement. High-energy efficient helicopter engines help decrease the environmental damage. Exergy should be applied to the system to determine the maximum available energy. In this study, energy analysis and exergy analysis have been applied to a turboshaft helicopter engine. According to the result of this study, the maximum energy and exergy efficiencies are found to be 21.99% and 15.87%, respectively, at 1500 Shaft Horsepower (SHP). It is seen that the efficiencies increase with the increase of the engine power. Besides, exergy destructions and exergy loss values are presented by calculating different powers

Koruyucu, Elif, Altuntas, Onder, Karakoc, T. Hikmet

Advanced Exergy Analysis of an Air Craft Gas Turbine Engine at Different Power Loading Operations

2019-01-1863

09/16/2019

The innovations in aircraft propulsion have been identified as the key parameter towards the progress in transportation. Continuous advancement in the performance and efficiency of propulsion has enabled aircraft to travel over larger distances with higher speed. Aviation is also responsible for approximately 2% of total greenhouse gas emission and is expected to grow around 3% by 2050. The present article aims to use the exergetic analysis of a turboprop engine which should be helpful in designing of such engines and also helps these engine users to regulate and select the operation modes. A gas turbine with film air cooling of turbine blades has been proposed to be the turboprop engine. The engine is analyzed on exergy point of view at different power loading operation modes and the performance is studied. Selected exergetic measures under consideration are Exergy Efficiency, Fuel Exergy Depletion Ratio, Relative Exergy Consumption Ratio, Exergetic Improvement potential and

Mohapatra, Alok Kumar, Hotta, Tapano, Choudhary, Tushar

Design Considerations for Enclosed Turboprop Engine Test Cells

AIR5295A (Current)

11/21/2018

This document is offered to provide state-of-the-art information about design factors that must be considered in the design of new or significantly modified engine test cells used to test propeller equipped turboprop engines in either QEC or bare engine configurations. The report does not address design considerations for test cells designed to test turboprop engines with dynamometer type load absorption devices because they are essentially tested as turboshaft engines. Design considerations for those test cells are presented in AIR4989, Reference 2.1

EG-1E Gas Turbine Test Facilities and Equipment

Aviation Oxygen Safety Management System Analysis

2018-01-600104/15/2018

Oxygen has been a significant variable in flight operations for nearly 60 years. Today, the use of oxygen is almost synonymous with rocket, jet and turbo-prop operations affecting more than 45,000 aircraft worldwide. Today’s pilot flies farther, higher and longer than ever before, and does so at an ever increasing frequency. While the past 60 years have yielded tremendous advances in propulsion, avionics, materials and many other areas, oxygen and its role in aviation has remained largely stagnant. Although considered a major aircraft system and an essential component in high altitude operations, the orthodox mantra of ‘engineering it better’ has produced only limited results, most of them in the area of dispensation equipment (masks). In recent years Aeronautical Data Systems and collaborative entities have begun working to create a standardized and comprehensive aviation oxygen safety management system. This paper includes a general examination of what a new aviation oxygen doctrine

Stabile, Jim

Thermoeconomic, Sustainability and Environmental Damage Cost Analysis of Air Cooled CT7-7A Turboprop Engine

2018-01-0774

04/03/2018

The aim of this study is to investigate the overall performance (exergetic, exergoeconomic and exergoenvironmental) of CT7-7A turboprop engine manufactured by General Electric Aviation (GE Aviation) and currently used to power CN-235, a medium range transport aircraft. The investigation has been carried out using the thermoeconomic, sustainability and environmental damage cost analysis methods. The adopted turboprop engine has been investigated to observe the behaviour of various performance parameters, sustainability, emission parameters as well as cost parameters of engine. Due to ever increasing demand in air transport systems, focus has been on developing efficient and sustainable systems with lowest possible cost. In order to reduce cost & environmental effects of engine and at same time to acquire higher performance, it is necessary to understand the mechanism that can offer improvements in the engine operating and design parameters so that higher performance can be obtained

Sahu, Mithilesh Kumar, Choudhary, Tushar, Kumari, Anupam, R, Sanjay

Thermodynamic Modeling of Blade Cooled Turboprop Engine Integrated to Solid Oxide Fuel Cell: A Concept

2018-01-1308

04/03/2018

In modern turboprop engines, reduction in emission and fuel consumption is the primary goals during the development of gas turbine aero engines. In this paper, a concept has been proposed for hybridizing the air blade cooled turboprop engines by integrating it with a fuel cell. The proposed study focuses on thermodynamic analysis of a turboprop engine integrated to a solid oxide fuel cell (SOFC) system. A solid oxide fuel cell is the perfect candidate for utilizing waste heat available at turboprop engine exhaust, through recuperation process. Integration of SOFC is ultimately leads to enhancement the overall performance of the turboprop-SOFC hybrid system. Power generated by the SOFC system can be utilized by the aircraft and in can complement the auxillary-power-unit (APU) and may even supplement it. On the basis of 1st and 2nd law of thermodynamic modeling analysis of a turboprop-SOFC system has been presented in this article. The adopted turboprop engine has operated under a wide

Choudhary, Tushar, Sahu, Mithilesh Kumar, R, Sanjay, Kumari, Anupam, Mohapatra, Alok

Installed Outdoor Engine Testing

AIR5301A (Historical)

11/29/2017

This SAE Aerospace Information Report (AIR) was written because of the growing interest in aircraft installed outdoor engine testing by the Federal Aviation Administration, airlines, charter/commercial operators, cargo carriers, engine manufacturers and overhaul and repair stations. This document was developed by a broad cross section of personnel from the aviation industry and government agencies and includes information obtained from a survey of a variety of operators of fixed and rotary wing aircraft and research of aircraft and engine maintenance manuals

EG-1E Gas Turbine Test Facilities and Equipment

Test Facility Shakedown and Commissioning

AIR6364 (Current)

11/29/2017

The paper discusses in general terms the activities required to be undertaken or demonstrated during the establishment of the facility such as: the assessment checks prior to forwarding to the end users site for embodiment into the facility system the establishment of the facility such as trial installations of hardware, functionality checking of lifting transportation and access systems, centerline pull checks, pressure testing of fuel and air start systems, flushing of wet systems and electrical continuity checking. the commissioning of the facility such as instrumentation calibrations, engine starts, engine running, assessment of command and control system, assessment of DAS system, aerodynamic and acoustic surveys. The paper will concentrate on the main engineering engine related aspects of the facility and will not necessarily contain information on the construction validation activities such as HVAC, electrical, facility fire system, waste water etc. Risk analysis may be

EG-1E Gas Turbine Test Facilities and Equipment

Exergoeconomic Analysis of Air Cooled Turboprop Engine: Air Craft Application

2017-01-2044

09/19/2017

Aircraft engines powering propulsion of the aircraft is the key component of the system. In aircraft industry it is desirable that an aircraft engines should supply high speeds (for military fighters) with low maintenance (for civil airplanes). In this regard an integration of gas turbine engines with traditional propeller has been introduced and termed as turboprop engine. In present work, a gas turbine with cooled blading has been proposed to be the turboprop engine which has been exergoeconomically analyzed to assess the performance and economics related to the proposed turboprop engine. Exergo-economic analysis is a tool which combines thermodynamic analysis and economic principles to provide information that is helpful to predict thermodynamic performance and total cost of the engine (thermal system). The methodology includes energy, exergy and cost balance equations for component-wise modelling of whole system. “Average Cost Theory” (Levelized cost) approach has been adopted to

Sahu, Mithilesh Kumar, Choudhary, Tushar, Y, Sanjay

MOBILITY ENGINEERING: March 2016

16MEIP0303/01/2016

Autonomous vehicles: impact on society Self-driving technology offers plenty of promise, but not everything about autonomous vehicles will be a panacea. Crankshaft reliability by integrated design, simulation, and testing This testing method is proven and beneficial for the design and development of the crankshaft and could be applied to other critical engine components, thereby extending to system reliability. New Engines 2016 Highlighting the design, engineering, and technologies inside some of the most competitive gasoline and light-duty diesel ICEs. Touch and go Avionics developments are changing life in the cockpit and at airborne work stations. Improving heavy-duty engine component efficiencies Cylinder deactivation can improve fuel economy by using a reduced number of cylinders that operate at higher loads and thermal efficiency, while other cylinders are turned off, when the engine operates at partial load conditions. A switching roller finger follower is one of the

GE's clean-sheet turboprop engine to launch with Textron Aviation

16MEIP03_0803/01/2016

Textron Aviation has opted for GE Aviation's all-new turboprop engine to power its single engine turboprop (SETP). The 1300 shaft horsepower (SHP)-rated turboprop engine will be the first entry in GE's new family of turboprop engines designed specifically for business and general aviation aircraft in the 850- to 1600-SHP range. Brad Mottier, Vice President and General Manager of GE Aviation's Business & General Aviation and Integrated Systems division, said during the recent announcement that “this new engine features an industry-best 16:1 overall pressure ratio (OPR), enabling the engine to achieve up to 20% less fuel consumption and 10% more cruise power compared to competitor offerings in the same size class, which usually feature an OPR of 9:1. It also has 4000-6000 hour MTBO,” or mean time between overhauls, which is about 30% longer than with existing engines

Broge, Jean L.

Fanjet Evolution — the Next Steps

TBMG-2188504/01/2015

The global aerospace sector has always represented the cutting edge of practical technology advancement. When the first military jet engines emerged in the post-war 1940s it was clear that commercial applications would soon follow. The leap in performance, payload capability, maintainability, and speed compared to the best that turbo-supercharged piston-engines could offer was truly revolutionary

Propulsion

15AERP04_0104/01/2015

Fanjet Evolution - the Next Steps Rolls-Royce is on a determined path to equip commercial airplanes over the coming decades with new engines that take advantage of engineering breakthroughs in materials and core architectures. The global aerospace sector has always represented the cutting edge of practical technology advancement. When the first military jet engines emerged in the post-war 1940s it was clear that commercial applications would soon follow. The leap in performance, payload capability, maintainability, and speed compared to the best that turbo-supercharged piston-engines could offer was truly revolutionary

Gardner, Richard

Europe's Aerospace Industry Looking Confident

TBMG-1975506/01/2014

Talk of further consolidation within Europe’s dynamic aerospace sector has been on the lips of industry watchers for several years, but although the major European-based global players have not progressed toward further mergers, the continent’s biggest aerospace company, the former EADS, has achieved a very significant business restructuring, sweeping all its diverse companies into one giant, three-division entity, and adopting the new corporate identity of the Airbus Group

Europe's Aerospace Industry Looking Confident

14AERP06_0106/01/2014

Apart from Airbus's highly visible presence in defense and commercial aircraft, Europe also has successful capabilities in helicopters, business jets, and aero engines, and in all these areas their global market share is growing. Talk of further consolidation within Europe's dynamic aerospace sector has been on the lips of industry watchers for several years, but although the major European-based global players have not progressed toward further mergers, the continent's biggest aerospace company, the former EADS, has achieved a very significant business restructuring, sweeping all its diverse companies into one giant, three-division entity, and adopting the new corporate identity of the Airbus Group. At one stage it looked as if a proposed merger between EADS and BAE Systems might create the world's largest combined aerospace and defense company, but a German political veto put an end to this plan, largely because of sensitivity over the defense aspects of such a deal

Gardner, Richard

Guide to Engine Lubrication System Monitoring

AIR1828B (Historical)

05/01/2014

The purpose of this SAE Aerospace Information Report (AIR) is to provide information and guidance for the selection and use of lubrication system monitoring methods. This AIR is intended to be used as a technical guide. It is not intended to be used as a legal document or standard. The scope of this document is limited to those inspection and analysis methods and devices that can be considered appropriate for routine maintenance

E-32 Aerospace Propulsion Systems Health Management

The Preparation and Use of Chromel-Alumel Thermocouples for Aircraft Gas Turbine Engines

AIR46B (Historical)

05/01/2014

This SAE Aerospace Information Report (AIR) reviews the precautions that must be taken and the corrections which must be evaluated and applied if the experimental error in measuring the temperature of a hot gas stream with a thermocouple is to be kept to a practicable minimum. Discussions will focus on Type K thermocouples. These are defined in NBS Monograph 125 as nickel-chromium alloy versus nickel-aluminum alloy thermocouples

E-32 Aerospace Propulsion Systems Health Management

Turboshaft/Turboprop Gas Turbine Engine Test Cell Correlation

ARP4755B (Historical)

12/19/2013

This paper describes a recommended practice and procedure for the correlation of test cells that are used for the performance testing of turboprop and turboshaft engines. This Aerospace Recommended Practice (ARP) shall apply to both dynamometer and propeller based testing. Test cell correlation is performed to determine the effect of any given test cell enclosure and equipment on the performance of an engine relative to the baseline performance of that engine

EG-1E Gas Turbine Test Facilities and Equipment

The big boys go for plastic

12AERD0613_0106/13/2012

While it is true that the latest developments in advanced alloy manufacturing techniques can deliver structures and components that meet all the product requirements that aerospace primes need for new aircraft, there can be no escaping the fact that there is now an unstoppable momentum building up for the plastic airplane. Composites have been around for many decades, but the promise of lighter and stronger structures has taken far longer to translate into significant mainstream civil aircraft production, beyond the general aviation, business jet, and defense communities. In the May 16 issue of Aerospace Engineering, we looked at the impact of composites on how large turbofan engines are built, but in the airframe sector, the shift has been gradual, with composites first replacing metal components on a one-to-one basis for simple structures, and where large angular sections could be molded in one piece, replacing the need for large numbers of separate sheets, strengthening fillets, and

Gardner, Richard

Guide to Limited Engine Monitoring Systems for Aircraft Gas Turbine Engines

AIR1873 (Historical)

03/28/2012

E-32 Aerospace Propulsion Systems Health Management

Test Cell Instrumentation

AIR5026A (Historical)

08/01/2011

This document discusses, in broad general terms, typical present instrumentation practice for post-overhaul gas turbine engine testing. Production engine testing and engine development work are outside the scope of this document as they will typically use many more channels of instrumentation, and in most cases will have requirements for measurements that are never made in post-overhaul testing, such as fan airflow measurements, or strain measurements on compressor blades. The specifications for each parameter to be measured, in terms of measurement range and measurement accuracy, are established by the engine manufacturers. Each test cell instrument system should meet or exceed those requirements. Furthermore, each instrument system should be recalibrated regularly, to ensure that it is still performing correctly

EG-1E Gas Turbine Test Facilities and Equipment

Innovation Fuels the Future of Air Travel

TBMG-1011206/01/2011

Aircraft of the future may not look significantly different from today’s aircraft, but a peek “under the hood” will reveal technologies that are vastly different. Commercial aviation giants such as Boeing and Airbus — in addition to NASA and academia — are developing breakthrough airframe, propulsion, materials, and cabin designs that will help aircraft of the future fly quieter, cleaner, and more fuel-efficiently, with enhanced passenger comfort

424-19 Navigation Systems Data Base

ARINC424-19 (Historical)12/18/2009

THE CURRENT VERSION OF THIS DOCUMENT IS 424-22. THIS PREVIOUS VERSION IS AVAILABLE FOR YOUR CONVENIENCE. This standard provides a data base comprising standards used for the preparation of a navigation system data base. This data may be used with the operational flight software in a wide range of navigational equipment

Airlines Electronic Engineering Committee

Installed Outdoor Engine Testing

AIR5301 (Historical)

11/15/2007

EG-1E Gas Turbine Test Facilities and Equipment

Design Considerations for Enclosed Turboprop Engine Test Cells

AIR5295 (Historical)

11/15/2007

EG-1E Gas Turbine Test Facilities and Equipment

Turboshaft/Turboprop Gas Turbine Engine Test Cell Correlation

ARP4755A (Historical)

11/15/2007

EG-1E Gas Turbine Test Facilities and Equipment

424-18 Navigation Systems Data Base

ARINC424-18 (Historical)11/23/2005

Airlines Electronic Engineering Committee

Aircraft Hydraulic Starter/Pumps

AS838 (Historical)

04/26/2005

This specification established (1) the common requirements for hydraulic units capable of functioning as starters and as pumps suitable for use in aircraft and missiles and (2) the methods to be used for demonstrating compliance with these requirements

A-6C4 Power Sources Committee

Dynamic Modal Analysis and Optimization of a Mechanical Sensor Arm Deployment System for a C-130 Aircraft

2004-01-312911/02/2004

During structural engineering design two of the most overlooked design facets of a finished product is understanding the behavior characteristics of how the product will react when resonated at its natural frequencies and actually defining and understanding the overall vibration profile responsible for the excitation of the structure. A C-130 mechanical arm/pod system has been developed to accommodate 1,000-pounds of sensor payload deployable in flight from a C-130 Hercules military aircraft (variants B thru J). The mechanical arm/pod system will be subjected to a profile of vibration from numerous sources during deployment and while in the final operating position. A general vibration profile for the mechanical arm/pod will be compiled from the plane’s four T-56-A-15 turboprop engines, the atmospheric turbulence and random gust loads. A pitot-accelerometer sensor probe was used to obtain vibration data of the C-130 ramp during a zero-light turbulence category flight for indicated

Wowczuk, Zenovy S., Means, Kenneth H., Mucino, Victor H., Thompson, Gregory J., Feragotti, Lawrence, Smith, James E., Naternicola, Adam, Corso, Bruce J.

Turbomachinery Blade Modal Analysis Using Contact Elements

2004-01-314111/02/2004

This paper presents a new methodology for analytically evaluating the natural frequencies and mode shape of a turbomachinery blade in an environment where friction phenomenon occurs. The blades analyzed in this study are unshrouded and located in the high-pressure turbine found in turbofan engines, and in the compressor turbine found in turboprop engines. The goal of this method is to correctly predict the modal parameters of the blade in order to determine whether there will be any resonance in the running range of the turbomachinery, and to more accurately predict the stresses at the blade-disc interface. This study was performed using ANSYS® contact elements. After comparison, the analytical results were found to agree with the experimental results. A convergence study was also performed, and it was found that only the friction coefficient and the surface contact stiffness had a considerable effect on the natural frequencies and mode shape convergence

Guerra, Mario, Thomas, Marc, St-Georges, Lyne

424-17 Navigation System Data Base

ARINC424-17 (Historical)08/31/2004

Airlines Electronic Engineering Committee

Engine Bleed Air Systems for Aircraft

ARP1796 (Historical)

06/22/2004

This ARP discusses design philosophy, system and equipment requirements, installation environment and design considerations for systems within the ATA 100 specification, Chapter 36, Pneumatic (reference 1). This ATA system/chapter covers equipment used to deliver compressed air from a power source to connecting points for other systems such as air conditioning, pressurization, anti-icing, cross-engine starting, air turbine motors, air driven hydraulic pumps, and other pneumatic demands. The engine bleed air system includes components for preconditioning the compressed air (temperature, pressure or flow regulation), ducting to distribute high or low pressure air to the using systems, and sensors/instruments to indicate temperature and pressure levels within the system. The engine bleed air system interfaces with the following ATA 100 systems: The interface with these systems/chapters is at the inlet of the shutoff/control valve of each associated system. This boundary definition aligns

AC-9 Aircraft Environmental Systems Committee

Simulating safety

AEROJAN04_0301/01/2004

Bombardier Aerospace simulates airflow in nacelles to prevent engine foreign-object damage. The potential for objects to be ingested into an aircraft's engine through the nacelle and possibly force the engine to be taken out of service for repairs is a concern with all airplane operators. Bombardier Aerospace has performed many physical experiments on its Q Series Dash 8 regional aircraft in an effort to eliminate foreign-object damage (FOD). The Q Series Dash 8 family of turboprop regional airliners includes the 37- passenger Q100 and Q200, the 50- to 56- passenger Q300, and the 68- to 78-passenger Q400, which had its first flight in 1998 and entered commercial service in February 2000. Two PW150A turboprop engines supplied by Pratt & Whitney Canada power the Bombardier Q400 aircraft. Each engine develops 5070 hp

An eye on UAVs

AEROAUG03_0408/01/2003

Electronics play an important role in unmanned aerial vehicles designated for intelligence, surveillance, and reconnaissance mission areas, as well as for combat. Roadmaps seem to be everywhere these days. Earlier this year, Dyke Weatherington, Deputy, Office of the Secretary of Defense, Unmanned Aerial Vehicle Planning Task Force, announced the release of the 2002 Unmanned Aerial Vehicle Roadmap. According to Weatherington, one of the specific purposes of the document, which looks out to 2027, is to identify “those near-term mission areas that can be impacted significantly by emerging UAV technology.” Another goal for the roadmap is its use as “a guide to our industry and allies, identifying the highest value areas for independent investment and areas for international cooperation,” said Weatherington. Ironically, it is international uncooperation that has made UAVs increasingly important for a wide range of armed forces mission scenarios-particularly ISR, or intelligence

Broge, Jean L.

424-16 Navigation System Data Base

ARINC424-16 (Historical)08/30/2002

Airlines Electronic Engineering Committee

Boundary Layer Control System; Pressure

AS81366 (Historical)

02/13/2002

This specification covers pressure boundary layer control systems of turbo-jet and turbo-prop aircraft for increasing the aerodynamic lift of the wings and flaps during approach, landing, and takeoff

Aerospace Council

Evaluation of an Unconventional Diesel Engine as a General Aviation Powerplant

2000-01-168505/09/2000

A novel two stroke cycle diesel engine is evaluated as a general aviation aircraft powerplant. Two certificated spark-ignited gasoline reciprocating engines are also evaluated in the same aircraft. The evaluation of aircraft propulsion performance considered only the effects of altered powerplant parameters on the range of an aircraft having a fixed gross weight and payload cruising at a given lift/drag ratio. Thermodynamic analysis finds the diesel engine can have a sea level power rating exceeding the 10,000 foot cruise power requirement by 55% with nearly equal specific fuel consumption, a low engine speed and a modest cylinder pressure. It uses a single-stage, radial turbocharger without intercooling or auxiliary mechanical scavenging. The diesel engine can significantly increase the range of a particular airplane now powered by a certificated turboprop engine. The candidate gasoline engines could not equal the turboprop-powered aircraft performance

Addoms, Robert

AC Starting Demonstration with Allison AE2100 Turboprop Engine

97122406/18/1997

During the month of October 1995, Auxilec successfully demonstrated its newly developped AC engine start concept on the Allison AE2100 turboprop engine. This demonstration took place at the AE2100 engine development test cell, which is located in Indianapolis, Indiana. The Auxilec AC engine start system included an off-the-shelf 3OkVA brushless generator, which was derived from an existing helicopter application, together with a vector-controlled power inverter, which was derived from an existing automotive application. The engine start system was powered either by an 80 VDC conventional power supply, or by four NiCad 24VDC/42Ah batteries connected in series and kept at ambient temperature conditions. During this engine start demonstration, which lasted two days, Auxilec managed to perform forty-four (44) successive starts. Of these forty-four (44) engine starts, seven (7) were powered by batteries, while the rest were powered by the 80 VDC power source. As part of this engine start

Devred, Hervé, Besnard, Jean Philippe, Martinez, Mario

TEST CELL INSTRUMENTATION

AIR5026 (Historical)

11/01/1996

This document discusses, in broad general terms, typical present instrumentation practice for post-overhaul gas turbine engine testing. Production engine testing and engine development work are outside the scope of this document; they will use many more channels of instrumentation, and in most cases will have requirements for measurements that are never made in post-overhaul testing, such as fan airflow measurements, or strain measurements on compressor blades. The specifications for each parameter to be measured, in terms of measurement range and measurement accuracy, are established by the engine manufacturers. Each test cell instrument system should meet or exceed those requirements. Furthermore, each instrument system should be recalibrated regularly, to ensure that it is still performing correctly

EG-1E Gas Turbine Test Facilities and Equipment

THE PREPARATION AND USE OF CHROMEL-ALUMEL THERMOCOUPLES FOR AIRCRAFT GAS TURBINE ENGINES

AIR46A (Historical)

11/01/1996

E-32 Aerospace Propulsion Systems Health Management

REPORT ON AIRCRAFT ENGINE CONTAINMENT

AIR1537A (Current)

08/01/1996

The study shall be directed to commercial aircraft service and include engine experience in both fixed wing aircraft and helicopters covering the time period from 1962 to the present

Engine Containment Ad Hoc Committee

GUIDE FOR DETERMINING ENGINE STARTER DRIVE TORQUE REQUIREMENTS

AIR781 (Current)

09/01/1994

A general discussion is presented herein, to outline the starter functions which are necessary for a successful engine start. In addition, sample calculations are included to illustrate an accepted method of determining the engine starting time from known data. Further consideration is then given to the relationship between starter torque output and engine pad strength and a generalized formula is presented for calculating the theoretical transient torque peaks for a simplified starter-engine system. Sample calculations for actual tests are included, and the results of these calculations are compared with measured values

AE-6 Starting Systems and Auxiliary Power Committee

Turboshaft/Turboprop Gas Turbine Engine Test Cell Correlation

ARP4755 (Historical)

03/01/1994

EG-1E Gas Turbine Test Facilities and Equipment

Philosophical Approach to the Basic Understanding of the Mechanics of Jet Propulsion

92096004/01/1992

This paper attempts to bring home the philosophy which lies behind the practical application of air-breathing and rocket engines. The various types of practical engines namely rocket engine, ram jet engine, turbojet engine, turbofan engine (mixed and unmixed exhausts), turboprop engine appear to be principally different. However philosophically, they are all one and the same. To appreciate this philosophy, let us change our frame of interest from the fluid to the jet engine. This leads us to the very first principles of jet propulsion i.e. the generation of thrust from the pressure forces exerted by the fluid on the boundaries and components of the jet engine. Well established mathematical concepts and relationships are available for practically estimating the performance of these engines based on fluid parameters. However philosophically, thrust and propulsive efficiency are sufficient for the philosophical understanding of the generation of variety of aircraft engines. A fluid exerts

Mahulikar, Shripad Prabhakar

GUIDE TO ENGINE OIL SYSTEM MONITORING

AIR1828A (Historical)

01/22/1992

The purpose of this SAE Aerospace Information Report (AIR) is to provide information and guidance for the selection and use of oil system monitoring devices and methods. This AIR is intended to be used as a technical guide. It is not intended to be used as a legal document or standard. The scope of this document is limited to those inspection and analysis methods and devices that can be considered appropriate for routine maintenance. In agreement with industry usage, wear particle size ranges are given in micrometers (1 μm = 10-3 mm = 10-6 m

E-32 Aerospace Propulsion Systems Health Management