Discussion

Started 1 March 2022

University of Engineering and Technology Taxila

IMPULSE TURBINE (Hydro-Turbine)

The runner of an impulse turbine is usually moved by the velocity of the water, and it discharges at atmospheric pressure. Each bucket on the runner is struck by a stream of water. The water falls out the bottom of the turbine housing after striking the runner because there is no suction on the down side of the turbine. In general, an impulse turbine is best for high-head, low-flow applications. Pelton and cross-flow turbines are the two primary forms of impulse turbines.

Turbine

Atmospheric Pressure

Mina Karimi-Avargani

Independent Researcher

Chuck A Arize

Texas A&M University – Commerce

Abdelkader BOUAZIZ

SOUGUEUR Division - Chemistry (POLYMERS), Université Ibn Khaldoun Tiaret

Sergey Voronin

Samara National Research University

Aqarab Husnain

University of Agriculture Faisalabad

How to optain Thrust Measurement in a Micro Gas Turbine Engine ?

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Asked 19 April 2025

Wisdom Simwila Kalunga

How can accurate thrust measurements be obtained for a micro gas turbine engine that is fixed to a static test bed during performance testing? I am exploring methods suitable for small-scale engines where direct force measurement is challenging due to low thrust levels. Are there preferred techniques or sensor arrangements (e.g., load cells, strain gauges, thrust stands) that provide reliable data without compromising structural integrity or introducing significant vibration errors? Insights on calibration procedures and data filtering methods for dynamic thrust output would also be appreciated.

"Guidance on Establishing a High-Standard Propulsion Laboratory at a University"

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Asked 26 January 2025

Wisdom Simwila Kalunga

I am planning to establish a state-of-the-art propulsion laboratory at a university, with the objective of supporting advanced research and teaching in aerospace and energy systems. The laboratory will focus on areas such as turbomachinery, jet propulsion, rocket propulsion, and combustion dynamics.

I seek advice on the following aspects from experts in the field:

2. *Instrumentation and measurement systems*: What kind of sensors, data acquisition systems, and diagnostic tools would be indispensable for accurate measurement and analysis (e.g., PIV, LDV, pressure transducers)?

3. *Infrastructure requirements*: What considerations should be given to facility design, such as vibration isolation, exhaust management, or high-temperature material handling?

4. *Best practices in designing experimental setups*: Are there any specific recommendations for optimizing experimental rigs for efficiency and scalability?

Any guidance, including references to successful propulsion labs, academic case studies, or suppliers of specialised equipment, would be greatly appreciated. Thank you!

"Designing a Turbocharger-Derived Turbojet Engine as a Durable Teaching Aid for Gas Turbine Operations"

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Asked 26 January 2025

Wisdom Simwila Kalunga

I am currently working on designing and building a turbocharger-derived turbojet engine as part of my final-year dissertation project. The primary objective of this engine is to serve as a high-quality teaching aid for demonstrating the fundamental operating principles and components of jet engines, such as the compressor, combustion chamber, turbine, and nozzle.

Given my aspiration to pursue an academic career and utilise this project for educating future university students, I aim to design an engine that is:

1. Durable and reliable for repeated demonstrations in a laboratory or classroom environment.

2. Comprehensive in functionality, showcasing key thermodynamic processes (e.g., Brayton cycle) and providing practical insights into gas turbine operations.

3. Scalable for various teaching applications, including advanced topics like thrust generation, efficiency analysis, and component-level modifications.

I seek advice and insights on the following:

1. Material selection and fabrication: What materials and manufacturing techniques would you recommend for creating a robust yet cost-effective teaching engine?

2. Instrumentation and diagnostics: What sensors and data acquisition systems should be integrated to measure and visualise parameters like thrust, fuel consumption, and exhaust temperature for educational purposes?

3. Turbocharger suitability: From your experience, are there specific turbocharger models or configurations that are better suited for conversion into turbojet engines? How do you recommend addressing challenges such as thermal stresses or achieving adequate thrust levels?

4. Future scalability: What design considerations should I incorporate to ensure this project can evolve into a more advanced teaching aid for broader academic use, such as hybrid propulsion systems or variable geometry components?

Your expertise and suggestions will be invaluable in refining my current project and ensuring its long-term viability as a teaching tool. Thank you in advance for your guidance!

Tags: Turbojet Engine, Turbocharger, Gas Turbine Operations, Teaching Aid, Propulsion Systems, Thermodynamics

How do you calculate the Power generation in steam Turbines??

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Asked 18 January 2025

Mahesh Wali

HOW DO YOU CALCULATE POWER GENERATION COST??Power in the steam Turbines produces at every stage where the steam is taken out, whether it may be bleed, extraction or exhaust steam. As the steam out from the turbine increases the power developed on that particular stage will increase.Power generation phenomenon.Power generation in steam Turbines is calculated based on difference between the heat content of inlet steam & extracted steam.📷Factors affecting the power generation:Power generation at particular stage increases, when there is more steam flow &vice versa Power generation at particular stage increases when there is more difference between inlet & extraction steam & Vice versa Power develop at particular stage decreases if its extraction pressure increases & vice versa Power developed at particular stage decreases if its extraction temperature increases & vice versa Power developed in steam Turbine decreases if inlet live steam pressure & temperature decrease If steam vacuum decreases power generation reduces or else Turbine will consume more steam to develop same power If exhaust steam temperature increases then the power power generation reduces or else Turbine will consume more steam to develop same power If wheel chamber pressure increases, then the power generation capacity of the Turbine decreases

In which part of the Turbine higher power can be produced at lower steam consumption? And why?

It is at the exhaust stage. Because at the exhaust stage pressure & temperature of the steam is very lesser than bleed &extraction stages.

In which part of the Turbine lowest power is produced at higher steam consumption? And why?

It is at the bleed stage. Because at bleed steam pressure & temperatures are higher than extraction & exhaust stages

Calculation part:

1-Calculate the power generated in a back pressure steam Turbine, where 50 TPH steam enters the Turbine at 66 kg/cm2 & temperature 485 Deg C.And steam exhausts to process at pressure 2 kg/cm2 & temperature 180 Deg C.

For calculation of power we need to know the enthalpy of inlet & exhaust steam.

Refer steam table

Enthalpy of inlet steam at rated parameters H1 = 806.5 kcal/kg

Enthalpy of inlet steam at rated parameters H2 = 677 kcal/kg

Now power developed in steam turbine P = Q X (H1-H2) / 860

Where Q is steam flow

P = 50 X (806.5-677) / 860

P = 7.52 MW

Note: 860 kcal = 1 KWH

-A Turbine’s inlet steam enthalpy is 825 kcal/kg & Exhaust enthalpy is 590 kcal/kg. Calculate the work done by steam & specific steam steam consumption

We have,

H1 = 825 kcal/kg, H2 = 590 kcal/kg

Work done per kg of steam = (H1-H2) = 825-890 =235 kcal/kg

SSC = 860 / Work done = 860 / 235 =3.65 kg/kwh or 3.65 MT/MW

6-A steam Turbine inlet steam pressure & temperatures are 104 kg/cm2 & 540 C0 & exhausts at pressure 0.09 kg/cm2 & temperature 43 Deg C calculate the

a- Work done per kg of steam

b- Heat supplied per kg of steam

c- Cycle efficiency

Enthalpy of inlet steam = 829 kcal/kg

Exhaust liquid enthalpy = 44 kcal/kg

Exhaust enthalpy by considering 90% dryness fraction = 44 + 0.9 X 616.44 =598.76 kcal/kg

A-Work done per kg of steam = (829-598.76) = 230.24 kcal/kg

B-Heat supplied per kg of steam = 829-44 = 785 kcal/kg

C-Cycle efficiency = Work done per kg of steam X 100 / Heat supplied per kg of steam

= 230.24 X 100 / 785 = 29.32%

Note:

Power developed at Generator terminals = Power developed at Turbine Shaft X Reduction gear box efficiency X Alternator efficiency

For example:

Calculate the net power developed at Generator terminal if 100 TPH steam enters the Turbine at 811 kcal/kg enthalpy & leaves the Turbine at enthalpy 565 kcal/kg .Assume Gear box efficiency as 98% & Generator efficiency as 95%

Power developed on Turbine shaft = 100 X (811-565) / 860 = 28.0 MW

Net power developed at Generator output terminals = 28.0 X 0.98 X 0.95 = 26.06 MW

Read more>>>https://www.powerplantandcalculations.com/2020/08/how-do-you-calculate-power-generation-in-steam-Turbines.html

www.powerplantandcalculations.com

Any ideas about how to define the sound sources generated by aeroacoustic processes?

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Asked 16 January 2025

Xiaolong Tang

The definition of aeroacoustic sources has been a widely debated topic since the introduction of Lighthill's equation. However, it seems that researchers have not yet identified a "true source" of sound generated by aeroacoustic processes, as compared to analogous sources. Perhaps the ResearchGate community would like to explore this topic further. We could discuss about it from the following two aspects:

(1) What properties should a true aeroacoustic source have?

(2) Are there any ideas or methods to derive or define such a source?

Essential Sizing For a TurboJet Engine Design Using a Turbocharger ?

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Asked 9 December 2024

Wisdom Simwila Kalunga

I am designing and manufacturing a turbojet engine based on a turbocharged system and require assistance with combustion chamber sizing, systems control for fuel and airflow regulation, and afterburner sizing to enhance performance and thrust. Additionally, I am researching fuel performance, comparing petroleum-based and alternative fuels, and need recommendations for cost-effective methods of data collection during testing, such as affordable sensors for measuring combustion efficiency, emissions, and thermal output. Any advice or resources on these design and research aspects would be greatly appreciated.

What are the key considerations for designing a control system and test rig setup for a turbocharger-based turbojet engine?

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Asked 8 December 2024

Wisdom Simwila Kalunga

I am currently working on the design and development of a turbojet engine using a turbocharger and need detailed guidance on the control and testing requirements. Specifically, I am seeking information on:

1. Components and instrumentation required for monitoring critical parameters such as thrust, fuel flow, exhaust gas temperature (EGT), and rotor speed.

2. Methods for designing a robust control system for throttle response, fuel injection, and operational stability across varying load conditions.

3. Test rig setup, including considerations for structural stability, vibration isolation, and safety measures for high-speed turbocharger operations.

4. Recommendations for data acquisition systems and software tools suitable for analysing engine performance during testing.

If you have experience in designing or testing turbojet engines, particularly those incorporating turbochargers, I would greatly appreciate any insights, methodologies, or references to enhance the precision and reliability of my project.

What are the critical design parameters and recommended methods for calculating and sizing an afterburner for a jet engine?

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Asked 8 December 2024

Wisdom Simwila Kalunga

What are the key design parameters for an afterburner, and are there recommended methods or tools for accurate calculations and sizing?

I am currently designing an afterburner for a jet engine project and seeking guidance on critical parameters for its design. Specifically, I would like to understand:

1. The optimal sizing and geometry of the afterburner for efficient thrust augmentation.

2. Key parameters such as fuel injection rate, flame stability, pressure drop, and temperature limits.

3. Methods for calculating the required airflow distribution and heat addition for various operating conditions.

4. Recommendations for simulation tools or empirical methods to predict performance, including combustion and thermal stresses.

If you have experience in designing or modelling afterburners, I would appreciate any insights, formulas, or references that could assist in improving the accuracy of my calculations and design.

Any Ideas on which Observation softwares for data collection during miniature Jet Engine test and simulation software for Combustion Chamber Design?

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Asked 8 December 2024

Wisdom Simwila Kalunga

What are the best simulation and analysis software tools for designing and testing miniature jet engines, specifically for a turbocharger-based jet engine combustion chamber capable of sustaining both conventional and alternative fuels?

I am working on my final-year project, where I aim to integrate a turbocharger into a jet engine design. A critical component of this project is the combustion chamber, which must efficiently handle various fuels, including kerosene-based aviation fuels and biofuels. I am looking for software tools that can simulate combustion dynamics, thermal stresses, and flow characteristics for small-scale engines.

Key features I need:

1. Support for multi-fuel combustion modelling (e.g., kerosene, biodiesel, hydrogen).

2. Detailed analysis of thermal and mechanical stresses.

3. Aerodynamic simulation of flow through the combustion chamber.

4. Compatibility with turbocharger dynamics.

If you have experience with such designs or simulations, I would greatly appreciate recommendations and insights into the accuracy, ease of use, and learning curves of these tools.

Small engine components test facility turbine testing cell

Article

Aug 1988

NASA Lewis Research Center has designed and constructed a new state-of-the-art test facility. This facility, called the Small Engine Components Test Facility (SECTF), is used to test gas turbines and compressors at conditions similar to actual engine conditions. The SECTF is comprised of two separate facilities - a turbine test cell and a compresso...

Numerical modelling of the sand particle flow in Pelton turbine injector

Article

Full-text available

May 2021

Pelton turbine is commonly employed high head impulse type turbine. Pelton turbine injector is an integrated part of the Pelton turbine machine which serves the purpose of converting entire pressure energy of water to kinetic energy and also regulates the water flowrate, with partial opening hence governing the power production. Severe erosion in P...

Nouvelle théorie de production de l'énergie exploitant les forces naturelles constantes, Etude d'une turbine gravitationnelle

Research Proposal

Full-text available

Nov 2021

Sadok Jabli

Dans cette étude, je proposerai une nouvelle théorie pour la production de l'énergie exploitant des forces naturelles constantes telles que la force gravitationnelle, la force de la pression atmosphérique, la force de la pression hydrostatique et même la force des aimants permanents. Je m'appuierai dans cette étude sur un nouveau système que j'ai i...

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IMPULSE TURBINE (Hydro-Turbine)

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