DOCSLIB.ORG

Section 4.3: the Ramjet Propulsion Cycle

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
Section 4.3: the Ramjet Propulsion Cycle Section 4.3: The RamJet Propulsion Cycle MAE 6530 - Propulsion Systems II Background on RamJets • Ramjets are a very simple jet engine configuration that are capable of high speeds • Ramjets cannot produce thrust at zero airspeed; they cannot move an aircraft from a standstill. • A ramjet powered vehicle, therefore, requires an assisted take-off like a rocket assist to accelerate it to a speed where it begins to produce thrust. • Inherently constrained to “combined cycle” applications for flight MAE 6530 - Propulsion Systems II Control Volume for a Ramjet ρ1V1 p2 V2 Tp p∞ 2e T T∞ e Ve V∞ ρe ρ∞ m! f = air m! fuel ! ! ! (mair + mfuel )⋅Vexit −(mair )⋅V∞ + Aexit ⋅( pexit − p∞ ) Fthrust = = p∞ ⋅ A0 ⎡⎛ ⎞ ⎤ ⎛ ⎞ f +1⎟ Vexit Aexit ⎜ pexit ⎟ F = m! ⋅V ⎢⎜ ⎟⋅ −1⎥ + ⋅⎜ −1⎟ thrust air ∞ ⎢⎜ f ⎟ V ⎥ A ⎜ p ⎟ ⎣⎝ ⎠ ∞ ⎦ 0 ⎝ ∞ ⎠ MAE 6530 - Propulsion Systems II Ideal Ramjet Thermodynamic Cycle Analysis Step 1-2 Step 3 Step 4 Region Process Ideal Behavior Real Behavior A to 1(inlet) Isentropic flow P0,T0 constant P0 drop ∞-1-2 (diffuser) Adiabatic P,T increase P0 drop Compression P0 drop 2-3 (burner) Heat Addition P0 constant, T0 P0 drop s Increase 3-4 (nozzle) Isentropic T0,P0 constant s Increase expansion MAE 6530 - Propulsion Systems II T0 drop 4 Ideal Ramjet Cycle Analysis (2) Step Process 1) Intake (suck) Isentropic Compression 2) Compress the Air (squeeze) Adiabatic Compression 3) Add heat (bang) Constant Pressure Combustion 4) Extract work (blow) Isentropic Expansion in Nozzle 5) Exhaust Heat extraction by surroundings Step 3 Step 1-2 Step 4 T-s Diagram Step 5 MAE 6530 - Propulsion Systems II 5 Cycle Efficiency of Ideal Ramjet 6 • Propulsive Power Output--> work perform by system in step 4 minus work required for step 1-2 • Net Heat Input --> heat input during step 3 (combustion) - heat lost in exhaust plume MAE 6530 - Propulsion Systems II 6 Cycle Efficiency of Ideal Ramjet (2) MAE 6530 - Propulsion Systems II 7 Cycle Efficiency of Ideal Ramjet (3) Add and Subtract From Right Hand Side MAE 6530 - Propulsion Systems II 8 Cycle Efficiency of Ideal Ramjet (4) • Assume … calorically perfect gasses à h ~ Cp•T • For conceptual simplicity … let … f >> 1 … and … Cpair ~ Cpproducts 9 MAE 6530 - Propulsion Systems II Cycle Efficiency of Ideal Ramjet (5) • From C-->D flow is isentropic … (Credit Narayanan Komerath, Georgia Tech) Step 1-2 Step 3 Step 4 MAE 6530 - Propulsion Systems II 10 Cycle Efficiency of Ideal Ramjet (6) • Approximate as Adiabatic compression across diffuser (Credit Narayanan Komerath, Georgia Tech) Step 1-2 Step 3 Step 4 MAE 6530 - Propulsion Systems II 11 Cycle Efficiency of Ideal Ramjet (7) • Sub (Credit Narayanan Komerath, Georgia Tech) into efficiency Step 1-2 Step 3 Step 4 equation MAE 6530 - Propulsion Systems II 12 Cycle Efficiency of Ideal Ramjet (8) (Credit Narayanan Komerath, Georgia Tech) Factor Out Step 1-2 Step 3 Step 4 MAE 6530 - Propulsion Systems II 13 Cycle Efficiency of Ideal Ramjet (9) (Credit Narayanan Komerath, Georgia Tech) Step 1-2 Step 3 Step 4 1. Cycle Efficiency Proportional to Inlet Pressure ratio, PB/PA 2. Cycle Efficiency Proportional to combustor temperature difference TC-TB 3. As inlet total pressure ratio (P0B/P0A) goes down … Cycle Efficiency Drops 4. Characteristic of a Brayton process, the cycle efficiency is anchored by the inlet compression process. MAE 6530 - Propulsion Systems II 14 Cycle Efficiency of Ideal Ramjet (10) (Credit Narayanan Komerath, Georgia Tech) Step 1-2 Step 3 Step 4 1. High Inlet Compression Ratio Desirable 2. Low Stagnation Pressure Loss Desirable 3. Large Temperature Change across Combustor Desirable 4. Ramjets Cannot Start from Zero Velocity MAE 6530 - Propulsion Systems II 15 Ideal Ramjet Example: Inlet and Diffuser • Take a Rocket motor and “lop the top off” • m fuel • normal • M > 1 m M < 1 m air shockwave air+fuel • Works Ok for subsonic, but for supersonic flow … can’t cram enough air down the tube • Result is a normal shock wave at the inlet lip MAE 6530 - Propulsion Systems II Ideal Ramjet Example: Inlet and Diffuser (2) • m fuel • normal • M > 1 m M < 1 m air shockwave air+fuel M ¥ M2 • Mechanical Energy is Dissipated into Heat • Huge Loss in Momentum MAE 6530 - Propulsion Systems II Ideal Ramjet Example: Inlet and Diffuser (3) • So … we put a spike in front of the inlet • m fuel Oblique shockwave • M > 1 m • air M < 1 m air+fuel Much weaker normal shockwave M∞ M2 • How does this spike Help? • By forming an Oblique Shock wave ahead of the inlet MAE 6530 - Propulsion Systems II 2-D Ramjet Inlet Example P0B M1=4.0 B b= 40° • Compare MB and P0 behind normal shockwaves B P0B Assume g=1.4 MAE 6530 - Propulsion Systems II 2-D Ramjet Inlet Example (3) P0B M1=4.0 B • From Normal Shock wave solver MAE 6530 - Propulsion Systems II 2-D Ramjet Inlet Example (4) = 40 deg. B • Across Oblique Shock wave π M n=0.5064 • M1n= M1 sin 1 = 4 sin ⎛ 40⎞ =2.571 2 ⎝180 ⎠ ⎛ 2 π ⎞ 2 ⎛4 sin2 ⎛ 40⎞ − 1⎞ 2 2 180 ⎜ ⎝ ⎝180 ⎠ ⎠ ⎟ 2{M1 sin (β) − 1} atan ⎜ ⎟ tan(θ) = → ⎜ ⎟ 2 π ⎛ ⎛ π ⎞ ⎞ ⎛ 2 ⎛ ⎛ π ⎞ ⎞ ⎞ tan(β)⎡2 + M1 ⎣⎡γ + cos(2β)⎦⎤⎤ ⎜ tan 40 2 + 4 1.4 + cos 2⋅40 ⎟ ⎣ ⎦ ⎝ ⎝ ⎝180 ⎠ ⎠ ⎝ ⎝ ⎝180 ⎠ ⎠ ⎠ ⎠ = 26.2 deg MAE 6530 - Propulsion Systems II 2-D Ramjet Inlet Example (5) = 40 deg. B • Across Oblique Shock wave 0.5064 M n =2.123 M n = 0.5064 → M = 2 = ⎛ π ⎞ 2 2 sin ⎝ (40 − 26.2) ⎠ sin(β1-θ) 180 P02/P0∞ = 0.4711 MAE 6530 - Propulsion Systems II 2-D Ramjet Inlet Example (6) = 40 deg. B • Across Oblique Shock wave ⎛ 1.4 ⎞ ⎜ ⎛ 1.4 − 1 2⎞ (1.4 − 1) ⎟ 0.3126 ⎜ ⎝1 + 4 ⎠ ⎟ ⎝ 2 ⎠ = 38.422 ⎛ 1.4 ⎞ ⎜ ⎛ 1.4 − 1 2⎞ (1.4 − 1) ⎟ ⎜ ⎝1 + 0.557853 ⎠ ⎟ MAE 6530 - Propulsion Systems II ⎝ 2 ⎠ 2-D Ramjet Inlet Example (7) M1=4.0 • Compare • Spike aids in increasing Total Pressure recovery Reducing “ram drag” M1=4.0 MAE 6530 - Propulsion Systems II 2-D Ramjet Inlet Example (8) MAE 6530 - Propulsion Systems II 2-D Ramjet Inlet Example (cont’d) MAE 6530 - Propulsion Systems II 2-D Ramjet Inlet Example (cont’d) MAE 6530 - Propulsion Systems II 2-D Ramjet Inlet Example (cont’d) MAE 6530 - Propulsion Systems II 2-D Ramjet Inlet Example (cont’d) • Compute efficiency …. Oblique shock inlet MAE 6530 - Propulsion Systems II 2-D Ramjet Inlet Example (cont’d) • Compute efficiency …. Oblique shock inlet M1=4.0 • Compute TC, TB T = 856.61 ºK C = TB = 1325.1ºK − (1.4 − 1) ⎛ ⎛ (1.4 − 1) ⎞ ⎞ 1.4 ⎜ ⎜ 1.4 ⎟ ⎟ 38.422 ⎜1325.1 − ⎜0.3126 ⎟ 856.61⎟ ⎝ ⎝ ⎠ ⎠ 1 − = 0.4652 1325.1 856.61 MAE 6530 - Propulsion Systems II ( − ) 2-D Ramjet Inlet Example (cont’d) • Compute efficiency …. Oblique shock inlet M1=4.0 = 0.2328 = 0.4652 M1=4.0 200% increase in efficiency! MAE 6530 - Propulsion Systems II Multi-stage Compression always Works Best For Stagnation Pressure Recovery! MAE 6530 - Propulsion Systems II MAE 6530 - Propulsion Systems II Questions?? MAE 6530 - Propulsion Systems II 34.
Load more

Recommended publications
  • Propulsion Systems for Aircraft. Aerospace Education II
    . DOCUMENT RESUME ED 111 621 SE 017 458 AUTHOR Mackin, T. E. TITLE Propulsion Systems for Aircraft. Aerospace Education II. INSTITUTION 'Air Univ., Maxwell AFB, Ala. Junior Reserve Office Training Corps.- PUB.DATE 73 NOTE 136p.; Colored drawings may not reproduce clearly. For the accompanying Instructor Handbook, see SE 017 459. This is a revised text for ED 068 292 EDRS PRICE, -MF-$0.76 HC.I$6.97 Plus' Postage DESCRIPTORS *Aerospace 'Education; *Aerospace Technology;'Aviation technology; Energy; *Engines; *Instructional-. Materials; *Physical. Sciences; Science Education: Secondary Education; Textbooks IDENTIFIERS *Air Force Junior ROTC ABSTRACT This is a revised text used for the Air Force ROTC _:_progralit._The main part of the book centers on the discussion -of the . engines in an airplane. After describing the terms and concepts of power, jets, and4rockets, the author describes reciprocating engines. The description of diesel engines helps to explain why theseare not used in airplanes. The discussion of the carburetor is followed byan explanation of the lubrication system. The chapter on reaction engines describes the operation of,jets, with examples of different types of jet engines.(PS) . 4,,!It********************************************************************* * Documents acquired by, ERIC include many informal unpublished * materials not available from other souxces. ERIC makes every effort * * to obtain the best copravailable. nevertheless, items of marginal * * reproducibility are often encountered and this affects the quality * * of the microfiche and hardcopy reproductions ERIC makes available * * via the ERIC Document" Reproduction Service (EDRS). EDRS is not * responsible for the quality of the original document. Reproductions * * supplied by EDRS are the best that can be made from the original.
    [Show full text]
  • The Power for Flight: NASA's Contributions To
    The Power Power The forFlight NASA’s Contributions to Aircraft Propulsion for for Flight Jeremy R. Kinney ThePower for NASA’s Contributions to Aircraft Propulsion Flight Jeremy R. Kinney Library of Congress Cataloging-in-Publication Data Names: Kinney, Jeremy R., author. Title: The power for flight : NASA’s contributions to aircraft propulsion / Jeremy R. Kinney. Description: Washington, DC : National Aeronautics and Space Administration, [2017] | Includes bibliographical references and index. Identifiers: LCCN 2017027182 (print) | LCCN 2017028761 (ebook) | ISBN 9781626830387 (Epub) | ISBN 9781626830370 (hardcover) ) | ISBN 9781626830394 (softcover) Subjects: LCSH: United States. National Aeronautics and Space Administration– Research–History. | Airplanes–Jet propulsion–Research–United States– History. | Airplanes–Motors–Research–United States–History. Classification: LCC TL521.312 (ebook) | LCC TL521.312 .K47 2017 (print) | DDC 629.134/35072073–dc23 LC record available at https://lccn.loc.gov/2017027182 Copyright © 2017 by the National Aeronautics and Space Administration. The opinions expressed in this volume are those of the authors and do not necessarily reflect the official positions of the United States Government or of the National Aeronautics and Space Administration. This publication is available as a free download at http://www.nasa.gov/ebooks National Aeronautics and Space Administration Washington, DC Table of Contents Dedication v Acknowledgments vi Foreword vii Chapter 1: The NACA and Aircraft Propulsion, 1915–1958.................................1 Chapter 2: NASA Gets to Work, 1958–1975 ..................................................... 49 Chapter 3: The Shift Toward Commercial Aviation, 1966–1975 ...................... 73 Chapter 4: The Quest for Propulsive Efficiency, 1976–1989 ......................... 103 Chapter 5: Propulsion Control Enters the Computer Era, 1976–1998 ........... 139 Chapter 6: Transiting to a New Century, 1990–2008 ....................................
    [Show full text]
  • Reusable Ram Booster Launch Design Emphasizes Use of Existing
    National Aeronautics and Space Administration technology opportunity Reusable Ram Booster Launch Design Emphasizes Use of Existing Components to Achieve Space Transport for Satellites and Spacecraft Using off-the-shelf technology to make space transport more affordable Engineers at NASA’s Dryden Flight Research Center have designed a partially reusable launch Benefits system to propel a payload-bearing spacecraft t Economical: Lowers the cost of space access, into a low Earth orbit (LEO). The concept design with use of reusable components and a simplified propulsion system for the three-stage Ram Booster employs existing turbofan engines, ramjet propulsion, and an already t Efficient: Maximizes use of already operational components by using off-the-shelf technology operational third-stage rocket to achieve LEO t Effective: Enables fast turnaround between missions, for satellites and other spacecraft. Excluding with reuse of recoverable first and second stages payload (which stays in orbit), over 97 percent t Safer: Operates with jet fuel in lower stages, of the Ram Booster’s total dry weight (including eliminating the need for hazardous hypergolic or cryogenic propellants and complex reaction three stages) is reusable. As the design also control systems draws upon off-the-shelf technology for many t Simpler: Offers a single fuel type for air-breathing of its components, this novel approach to space turbofan and ramjet engines transport dramatically lowers the cost of access to t Novel: Approaches space launch complexities space. The technology has applications for NASA, in a new way, providing a conceptual technical breakthrough for first and second stage boost the military, and the commercial aerospace sectors.
    [Show full text]
  • 04 Propulsion
    Aircraft Design Lecture 2: Aircraft Propulsion G. Dimitriadis and O. Léonard APRI0004-­1, Aerospace Design Project, Lecture 4 1 Introduction • A large variety of propulsion methods have been used from the very start of the aerospace era: – No propulsion (balloons, gliders) – Muscle (mostly failed) – Steam power (mostly failed) – Piston engines and propellers – Rocket engines – Jet engines – Pulse jet engines – Ramjet – Scramjet APRI0004-­1, Aerospace Design Project, Lecture 4 2 Gliding flight • People have been gliding from the-­ mid 18th century. The Albatross II by Jean Marie Le Bris-­ 1849 Otto Lillienthal , 1895 APRI0004-­1, Aerospace Design Project, Lecture 4 3 Human-­powered flight • Early attempts were less than successful but better results were obtained from the 1960s onwards. Gerhardt Cycleplane (1923) MIT Daedalus (1988) APRI0004-­1, Aerospace Design Project, Lecture 4 4 Steam powered aircraft • Mostly dirigibles, unpiloted flying models and early aircraft Clément Ader Avion III (two 30hp steam engines, 1897) Giffard dirigible (1852) APRI0004-­1, Aerospace Design Project, Lecture 4 5 Engine requirements • A good aircraft engine is characterized by: – Enough power to fulfill the mission • Take-­off, climb, cruise etc. – Low weight • High weight increases the necessary lift and therefore the drag. – High efficiency • Low efficiency increases the amount fuel required and therefore the weight and therefore the drag. – High reliability – Ease of maintenance APRI0004-­1, Aerospace Design Project, Lecture 4 6 Piston engines • Wright Flyer: One engine driving two counter-­ rotating propellers (one port one starboard) via chains. – Four in-­line cylinders – Power: 12hp – Weight: 77 kg APRI0004-­1, Aerospace Design Project, Lecture 4 7 Piston engine development • During the first half of the 20th century there was considerable development of piston engines.
    [Show full text]
  • An Online Performance Calculator for Ramjet, Turbojet, Turbofan, and Turboprop Engines
    An Online Performance Calculator for Ramjet, Turbojet, Turbofan, and Turboprop Engines Evan P. Warner∗ Virginia Tech, Blacksburg, VA, 24061, USA This paper documents the theory, equations, and assumptions behind an HTML-based online performance calculator for ramjet, turbojet, turbofan, and turboprop engines. Based on inputs of design parameters, flight con- ditions, and engine parameters, the specific thrust (()), thrust specific fuel consumption ()(), propulsive efficiency ([ ?), thermal efficiency ([Cℎ), and overall efficiency ([0) will be output for the engine of interest. Several sample cases are analyzed to verify the functionality of the calculator. These sample cases are derived from engines associated with Virginia Tech, which include: Pratt & Whitney’s PT6A-20 and JT15D-1, Honeywell’s TFE731-2B, and the Rolls Royce Trent 1000. With the help of this calculator, students will now be able to verify their air-breathing jet engine performance value calculations. This calculator is available here. I. Nomenclature "0 = Ambient Mach Number 2 ?1 = Specific Heat of the Burner W0 = Ambient Specific Heat Ratio 2 ?C = Specific Heat of the Turbine W3 = Diffuser Specific Heat Ratio 2 ? 5 = Specific Heat of the Fan W2 = Compressor Specific Heat Ratio )0 = Ambient Static Temperature W1 = Burner Specific Heat Ratio ?0 = Ambient Static Pressure WC = Turbine Specific Heat Ratio ?4 = Exit Static Pressure W= = Nozzle Specific Heat Ratio '08A = Gas Constant for Air W 5 = Fan Specific Heat Ratio '?A>3 = Gas Constant for the Products of Fuel/Air Mixture W= 5 = Fan Nozzle
    [Show full text]
  • Bussard Ramjet Was Presented in 1977 [8]
    TVIW 2016 Three Interstellar Ram Jets Albert A. Jackson . 73 TVIW 2016 Three Interstellar Ram Jets ALBERT ALLEN JACKSON IV Lunar and Planetary Institute, 3600 Bay Area Blvd, Houston, TX 77058, USA. Abstract The mass ratio problem in interstellar flight presents a major problem[1,[2}; a solution to this is the Interstellar Ramjet[3]. An alternative to the Bussard Ramjet was presented in 1977 [8]. The Laser Powered Interstellar Ramjet, LPIR. This vehicle uses a solar system based laser beaming power to a vehicle which scoops interstellar hydrogen and uses a linear accelerator to boost the collected particle energy for propulsion. This method bypasses the problem of using nuclear fusion to power the ramjet. Engine mass is off loaded to the beaming station. Not much work has been done on this system in last 40 years. Presented here are some ideas about boosting the LPIR with a laser station before engaging the ram mode, using a time dependent power station to keep the LPIR under acceleration. Fishback[4] in 1969 calculated important limitations on the ramjet magnetic intake, these considerations were augmented in a paper by Martin in 1973[6]. Fishback showed there was a limiting Lorentz factor for an interstellar ramjet. In 1977 Dan Whitmire [7] made progress towards solving the fusion reactor of the interstellar ramjet by noting that one could use the CNO process rather than the PP mechanism. Another solution to fusion reactor limitations is to scoop fuel from the interstellar medium , carry a reaction mass , like antimatter, combine to produce thrust [9,10,11].
    [Show full text]
  • A Method for Performance Analysis of a Ramjet Engine in a Free-Jet Test Facility and Analysis of Performance Uncertainty Contributors
    University of Tennessee, Knoxville TRACE: Tennessee Research and Creative Exchange Masters Theses Graduate School 5-2012 A Method for Performance Analysis of a Ramjet Engine in a Free- jet Test Facility and Analysis of Performance Uncertainty Contributors Kevin Raymond Holst [email protected] Follow this and additional works at: https://trace.tennessee.edu/utk_gradthes Part of the Other Mechanical Engineering Commons, and the Propulsion and Power Commons Recommended Citation Holst, Kevin Raymond, "A Method for Performance Analysis of a Ramjet Engine in a Free-jet Test Facility and Analysis of Performance Uncertainty Contributors. " Master's Thesis, University of Tennessee, 2012. https://trace.tennessee.edu/utk_gradthes/1163 This Thesis is brought to you for free and open access by the Graduate School at TRACE: Tennessee Research and Creative Exchange. It has been accepted for inclusion in Masters Theses by an authorized administrator of TRACE: Tennessee Research and Creative Exchange. For more information, please contact [email protected]. To the Graduate Council: I am submitting herewith a thesis written by Kevin Raymond Holst entitled "A Method for Performance Analysis of a Ramjet Engine in a Free-jet Test Facility and Analysis of Performance Uncertainty Contributors." I have examined the final electronic copy of this thesis for form and content and recommend that it be accepted in partial fulfillment of the equirr ements for the degree of Master of Science, with a major in Aerospace Engineering. Basil N. Antar, Major Professor We have read
    [Show full text]
  • Introduction to Airbreathing Propulsion Systems
    Introduction to airbreathing propulsion systems Integrated project: AIAA aircraft design competition 1er master Aerospace 2020 Koen Hillewaert, Université de Liège Design of Turbomachines, A&M [email protected] Remy Princivalle, Principal Engineer, Safran Aero Boosters [email protected] 1. Balances, thrust and performance Drag / thrust definition 1. Balances, thrust and performance Airbreathing engines: acceleration of (clean) air mass flow ● Thrust = acceleration force of engine mass flow from flight vf to jet velocity vj ● Powers – Propulsive power → airplane acceleration : – Mechanical power → fluid acceleration : – Lost power ● Propulsive efficiency: ● Increasing propulsive efficiency for constant thrust – increase mass flow, decrease jet velocity – Ingest flow at speed lower than flight speed 1. Balances, thrust and performance Airbreathing engines: Boundary Layer Ingestion ● ● 1. Balances, thrust and performance Airbreathing engines: classical performance parameters ● Thermal energy ! = mf Δhf – Fuel mass flow rate: – Fuel to air ratio: – Fuel lower heating value: ● "verall efficiency propulsive power Pp versus thermal energy ! – Propulsive efficiency: – Thermal efficiency: ● Efficiency $ Thrust specific fuel consumption (TSFC) ● Compacity $ Specific thrust 2. Jet engines Generation of high” speed "et through e#pansion over no%%le Snecma/'' (lympus 593 Afterburning ,urbo"et -./ Leap -i$il ,urbofan Snecma /88 Afterburning Turbofan 2. Jet engines Generation of high” speed "et through e#pansion over no%%le ● Ingestion of ma air at flight speed in nacelle – Ram effect: increased total T and p due to relative Mach num!er Mf ● Increase total pressure and temperature – Mechanical : fan – Thermal : gas generator " #rayton – $fter!urning ● #(pansion over e(haust noz)le to ambient pressure – %ho&ed – $dapted 2. Jet engines -ore flow: Brayton thermodynamic cycle ● Thermodynamic cycle – $dia!atic compression ' → ( : – %om!ustion ( → ) : – $dia!atic e*pansion )+, : 2.
    [Show full text]
  • A Design Study of Single-Rotor Turbomachinery Cycles
    A Design Study of Single-Rotor Turbomachinery Cycles by Manoharan Thiagarajan A thesis submitted to the faculty of the Virginia Polytechnic Institute and State University in partial fulfillment of the requirements for the degree of Master of Science in Mechanical Engineering Committee Dr. Peter King, Chairman Dr. Walter O’Brien, Committee Member Dr. Clint Dancey, Committee Member August 12, 2004 Blacksburg, Virginia Keywords: Auxiliary power unit, single radial rotor, specific power takeoff, compressor, burner, turbine A Design Study of Single-Rotor Turbomachinery Cycles by Manoharan Thiagarajan Dr. Peter King, Chairman Dr. Walter O’Brien, Committee Member Dr. Clint Dancey, Committee Member (ABSTRACT) Gas turbine engines provide thrust for aircraft engines and supply shaft power for various applications. They consist of three main components. That is, a compressor followed by a combustion chamber (burner) and a turbine. Both turbine and compressor components are either axial or centrifugal (radial) in design. The combustion chamber is stationary on the engine casing. The type of engine that is of interest here is the gas turbine auxiliary power unit (APU). A typical APU has a centrifugal compressor, burner and an axial turbine. APUs generate mechanical shaft power to drive equipments such as small generators and hydraulic pumps. In airplanes, they provide cabin pressurization and ventilation. They can also supply electrical power to certain airplane systems such as navigation. In comparison to thrust engines, APUs are usually much smaller in design. The purpose of this research was to investigate the possibility of combining the three components of an APU into a single centrifugal rotor. To do this, a set of equations were chosen that would describe the new turbomachinery cycle.
    [Show full text]
  • An Overview of Propulsion Systems for Flying Vehicles
    FOI-R--1563--SE June 2005 ISSN 1650-1942 Technical report Anders Hasselrot, Björn Montgomerie An Overview of Propulsion Systems for Flying Vehicles Source: Kanda and Kudo (2002) Systems Technology SE-172 90 STOCKHOLM SWEDISH DEFENCE RESEARCH AGENCY FOI-R--1563--SE Systems Technology June 2005 SE-172 90 Stockholm ISSN 1650-1942 Technical report Anders Hasselrot, Björn Montgomerie An Overview of Propulsion Systems for Flying Vehicles Issuing organization Report number, ISRN Report type FOI – Swedish Defence Research Agency FOI-R--1563--SE Technical report Systems Technology Research area code SE-172 90 Stockholm 7. Vehicles Month year Project no. June 2005 E83 0058 Customers code 5. Contracted Research Sub area code 73 Aeronautical Research Author/s (editor/s) Project manager Anders Hasselrot Fredrik Haglind Björn Montgomerie Approved by Monica Dahlén Sponsoring agency FMV Scientifically and technically responsible Anders Hasselrot, Björn Montgomerie Report title An Overview of Propulsion Systems for Flying Vehicles Abstract This report presents an overview of propulsion systems for flying vehicles, based on literature studies on current and future technologies. This effort is motivated by the need of this kind of information for the studies of vehicle concepts, being pursued in order to evaluate their performance merits. General information on inlets and outlets are also presented, as these influence the geometry and performance of the vehicles. The overview of inlet types is given with respect to the requirements at various Mach number regimes that govern the design. The stealth aspects are also viewed. In the report the available propulsion principles are presented category-wise, where most are based on combustion according to the Brayton cycle (heat addition under constant-pressure) and the other are based on combustion according to the Humphrey cycle (heat addition under constant-volume).
    [Show full text]
  • Ramjet-Propulsion-Talk-1947.Pdf
    __ ._1. ~'- " ;,:{ I ~,"'\'''' COpy NO. - . .....' I t~h1~",<~<,'NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS RAM JET PROPULSION ,r.. By Abe Silverstein ~ I [ Flight Propulsion Research Laboratory I' Cleveland, Ohio June 1947 C-L!\E.~~;IFlCATlON CHANGED Te, L2JC 1t.SSJFIED i\·~fI'\~(>~:T.TY 1ir~, H.~ L (; D2yc.r';':;J C:;~1[!.:..\rre # 6(4 n~'I'j:;' "".-' -.. OJ ') ',q l::l - . ' ... ~' ,J '-'."'_~ .c.). ~,.J __ liLH,.L C LAS S I FIE D DOC U MEN T ~,t1.'.nl~,-,i1J:t.h~e~:n'I~~,-r} ".'.';nt"ains class i£ied ir:forn,atior. affec­ to persons in the mili tary and naval Services of the 1.'·li-... , .la"lonaIDere~ o"t>' U'tdS ..... 't "1' ff' d ~-tbe-~'.J..:e:an:r:·:";:':-'f . J. ~,~e r lie nl e tates V?l1.rnn Unl1.ed States, apprcprla e C~Vl lan 0_ leers an ern­ ," ~ . n. 0 tho E~Plonage Act, esc 50:31 and 32. ployees of the Federal Government who have a legit­ tne revelation Df its contents in lmate lnte~est therein, and to United States oitizens cltnorized persoD. is .jlr:p_h)b~.teq.. bj.., '" of known loyal ty and discretiDn who of r.ecessi t"j rr:ust ":"c" _'" classified mf0~~!~:~:~f:'~;:~~2,:~:.:t:;f9X~~d.. t~~reOf. I~N~Bt:lIE"NJ "'~'" :~. ;~~-;~-,;~;:-':;;.;::::,:::,.-6~>~" I"A E,o: . ,or:,,: ;' . "-:<'- CONFIDENTIAL LECTURE FOR NEW DEVELOPMENTS DIVISION AIR COM1'1A.ND AND STAFF SCHOOL, AIR UNIVERSITY MAXWELL FIELD, AL.!\B.AH.l\. January 30, 1947 RAM JET PROPULSION By Abe Silverstein Flight Propulsion Eesearch Laboratory National Advisory Committee for Aeronautics Cleveland, Ohio COlllFIDENTIAL I i -,,-~--,",,~y'·q-,.,.~~~1t~---;;~:.-t"-:i±·,'~~l£~Gio':~"<i':;'"~'-"~';i~~~~-;'T"-:~'-~';~~:~~ .
    [Show full text]
  • Propulsion Operational Envelopes, Standard Atmosphere Air-Breathing Engines Aircraft Performance Rocket Engines
    Lecture #1 Ehsan Roohi Ferdowsi University of Mashhad Mechanical Engineering Group 1 Propulsion Operational Envelopes, Standard Atmosphere Air-breathing Engines Aircraft Performance Rocket Engines 2 References: 1- Element of Propulsion, Gas turbine and rockets, By: Mattingly 2- Mechanics and Thermodynamics of Propulsion, By: Hill and Peterson We read: o Introduction to aircraft and rocket propulsion (Chapter 1), o Review of fundamentals (Chapter 2), o Rocket Propulsion (Chapter 3) o Analysis and performance of air-breathing propulsion systems (Chapter 4-8), o Analysis and design of gas turbine engine components (Chapters 9 and 10). 3 Propel :"to drive, or cause to move, forward or onward. '‘ Study of propulsion includes the study of the propelling force, the motion caused, and the bodies involved. Propulsion involves an object to be propelled plus one or more additional bodies, called propellant. Methods devised to produce a thrust force for the propulsion are based on the principle of jet propulsion (the momentum change of a fluid by the propulsion system). The fluid may be the gas used by the engine itself (turbojet), it may be a fluid available in the surrounding (air used by a propeller), or it may be stored in the vehicle and carried by it during the flight (e.g., rocket). 4 Jet propulsion systems can be subdivided into two broad categories: air-breathing and non-air-breathing. Airbreathing propulsion systems include the reciprocating, turbojet, turbofan, ramjet, turboprop, and turboshaft engines. Non-airbreathing engines include rocket motors, nuclear propulsion systems, and electric propulsion systems. 1) Basic concepts and one-dimensional gas dynamics, 2) Analysis and performance of airbreathing propulsion systems, 3) Analysis of gas turbine engine components.
    [Show full text]