Different Types of Rocket Nozzles

Total Page:16

File Type:pdf, Size:1020Kb

Different Types of Rocket Nozzles Different Types of Rocket Nozzles 5322- Rocket Propulsion Project Report By Patel Harinkumar Rajendrabhai(1001150586) 1. Introduction 1.1 What is Nozzle and why they are used? A nozzle is a device designed to control the direction or characteristics of a fluid flow (especially to increase velocity) as it exits (or enters) an enclosed chamber or Pipe[9]. Nozzles are frequently used to control the rate of flow, speed, direction, mass, shape, and/or the pressure of the stream that emerges from them. In nozzle velocity of fluid increases on the expense of its pressure energy. A Water Nozzle[9] Rotator Style Pivot Sprinkler[9] 1.2 What is Rocket Nozzle? A rocket engine nozzle is a propelling nozzle (usually of the de Laval type) used in a rocket engine to expand and accelerate the hot gases from combustion so as to produce thrust according to Newton’s law of motion. Combustion gases are produced by burning the propellants in combustor, they exit the nozzle at very high Speed (hypersonic). 1.3 Properties of Rocket Nozzle Nozzle produces thrust. Exhaust gases from combustion are pushed into throat region of nozzle. Throat is smaller cross-sectional area than rest of engine, gases are compressed to high pressure. Nozzle gradually increases in cross-sectional area allowing gases to expand and push against walls creating thrust. Convert thermal energy of hot chamber gases into kinetic energy and direct that energy along nozzle axis.[1] Mathematically, ultimate purpose of nozzle is to expand gases as efficiently as possible so as to maximize exit velocity.[1] Rocket Engine[1] F m eVe Pe Pa Ae Neglecting Pressure losses F m eVe 2 Different types of Rocket Nozzle Configuration(shape) The rocket nozzles can have many shapes configurations. On the bases of there shapes they can be classified in three groups. 3 primary groups of nozzle types[2,3] 1. Cone (conical, linear) 2. Bell (contoured, shaped, classic converging-diverging) 3. Annular (spike, aerospike, plug, expansion, expansion-deflection)[1] 2.1 Conical nozzles[1,2,3] The conical nozzle is the oldest and the simplest configuration. It is ease to fabricate. The cone gets its name from the fact that the walls diverge at a constant angle. A small angle produces greater thrust, because it maximizes the axial component of exit velocity and produces a high specific impulse (a measure of rocket efficiency). Small nozzle divergence angle means long length and axial momentum and thus high specific impulse. It has penalty in rocket propulsion system mass, vehicle mass due to its long length. Large divergence angle reduces size and weight. But, results in performance loss at low altitude as the high ambient pressure causes overexpansion and flow separation. In practice the thrust, exist velocity, etc obtained from the ideal rocket equations are not the same. So, some correction factor has to be applied to this equations. The correction factor applied is called divergence factor and is denoted by Greek alphabet Lambda(λ). The expression for the divergence factor is given by 1/ 2*(1 cos) α is the half cone angle. λ = 1 for ideal rocket. For a nozzle with divergence angle of 30 deg. The value of α is 15 deg. Variation of correction factor with α is shown[2]. All 3 nozzles have same Ae/A* Red dashed lines indicate contours of normal flow[1] Flow is almost entirely axial (Best is uniform axial flow) Flow is mostly axial Flow has significant radial component Highly subject to separation 8 The design consist of an arc section which begins at throat. The arc section is followed by linear section with half cone angle α. The linear section has length L, which can be calculated mathematically as, 2 * Ae Where area * D 1 Ae D 2L tan * ratio is given by A * * L A D 2 tan Where, D* is the throat diameter. Ae/A* is the ratio of exit area to throat area. α is half cone angle. 2.2 Bell/Contoured Nozzle[3,4] Bell nozzle designs are similar to conical nozzle design but are more efficient and more compact than a conical nozzle. The bell nozzle is the most commonly used nozzle shape today. It is more advantages over the conical nozzle in terms of both, size and performance. It is Contoured to minimize turning and divergence losses. Reducing divergence requires more turning flow (more axial) which can result in compressions which in tern could lead to shock losses. This type of nozzles are designed such that all waves are isentropic and produce nearly axial flow at exit. The expansion in the supersonic bell nozzle is more efficient than in a simple straight cone of similar area ratio and length, because the wall contour is designed to minimize losses, as explained later in this section[2]. As shown bellow, the nozzle consists of two sections. Near the throat, the nozzle diverges at a relatively large angle(20 to 50 degree) (1) but the degree of divergence decreases downstream. Near the nozzle exit, the divergence angle is very small(less than 10) (2). The bell nozzle is a compromise between the two extremes of the conical nozzle since it minimizes weight while maximizing performance. The most important design issue is to contour the nozzle to avoid oblique shocks and maximize performance. This types of nozzle shapes are only optimum at one altitude conditions. 2 1 Bell Nozzle[1] Modern Day Bell Nozzle[11] The divergence loss at the exit of a bell nozzle is significantly less than that for a conical nozzle of the same design. The exit angle for a 15 degree conical nozzle is 15 degrees, while the exit angle of a Bell nozzle with the same exit diameter is only 8.5 degrees. This can be seen in Fig. below. Also the bell nozzle is shorter and has less mass than the conical nozzle because it is more compact. These characteristics make a Bell nozzle much more efficient than a straight conical nozzle[6]. Comparison of conical nozzle with bell nozzle[2] A change of flow direction of a supersonic gas in an expanding wall geometry can only be achieved through expansion waves. An expansion wave occurs at a thin surface, where the flow velocity increases and changes its flow direction slightly, and where the pressure and temperature drop. Wave surfaces are at an oblique angle to the flow. As the gas passes through the throat, it undergoes a series of these expansion waves with essentially no loss of energy. In the bell-shaped nozzle shown in Fig. these expansions occur internally in the flow between the throat and the inflection location I. the area is steadily increasing like a flare on a trumpet. The contour angle Ɵi is a maximum at the inflection location. Between the inflection point I and the nozzle exit E. The purpose of this last segment of the contoured nozzle is to have a low divergence loss as the gas leaves the nozzle exit plane. The difference between Ɵi and 0e is called the turn-back angle. When the gas flow is turned in the opposite direction (between points I and E) oblique compression waves will occur. These compression waves are thin surfaces where the flow undergoes a mild shock. The flow is turned, and the velocity is actually reduced slightly. Each of these multiple compression waves causes a small energy loss. It is possible to balance the oblique expansion waves with the oblique compression waves and minimize the energy loss with the help of Method of characteristics. The first set of curves[2] given below(left) gives the relation between length, area ratio, and the two angles of the bell contour. The second set of curves[2] given below(right) gives the correction factors, equivalent to the 2 factor for conical nozzles, which are to be applied to the thrust coefficient or the exhaust velocity, provided the nozzles are at optimum expansions, that is, P2 = P3. 2.3 Annular Nozzle[1,3] The annular nozzle, also sometimes known as the plug or "altitude-compensating" nozzle, is the least employed of those discussed due to its greater complexity. The term "annular" refers to the fact that combustion occurs along a ring, or annulus, around the base of the nozzle. "Plug" refers to the centerbody that blocks the flow from what would be the center portion of a traditional nozzle. "Altitude-compensating" is sometimes used to describe these nozzles since that is their primary advantage, a quality that will be further explored later. Expansion ratio: area of centerbody must be taken into account A A exit plug Athroat Another parameter annular diameter ratio, Dplug / Dthroat Ratio is used as a measure of nozzle geometry for comparison with other plug nozzle shapes There are two major types of annular nozzles developed to date. They are distinguished by the method in which they expand exhaust: (1) outward or (2) inward Radial Out-Flow Nozzles : Examples of this type are the expansion-deflection (E-D), reverse-flow (R-F), and horizontal-flow (H-F) nozzles Radial In-Flow Nozzles : Spike nozzles, linear-aerospike nozzle. Annular nozzles receiving significant research attention Several publications call these concepts ‘new’, but in actual, these ideas have been around for quite some time. These are the most complicated nozzles and hence have serious challenges with its implementation 16 2.3.1 RADIAL OUT-FLOW NOZZLES[1,3] Picture shows an example of an Expansion-Deflection (E-D) nozzle. Expansion-deflection nozzle works much like a bell nozzle. Exhaust gases forced into a converging throat before expanding in a bell-shaped nozzle Flow is deflected by a plug, or centerbody, that forces the gases away from center of nozzle and to stay attached to nozzle walls Centerbody position may move to optimize performance As altitude or back-pressure varies, flow is free to expand into ‘void’ This expansion into void allows the nozzle to compensate for altitude Pe adjusts to Pb within nozzle 17 Name of each of these nozzles indicates how it functions.
Recommended publications
  • Rocket Nozzles: 75 Years of Research and Development
    Sådhanå Ó (2021) 46:76 Indian Academy of Sciences https://doi.org/10.1007/s12046-021-01584-6Sadhana(0123456789().,-volV)FT3](0123456789().,-volV) Rocket nozzles: 75 years of research and development SHIVANG KHARE1 and UJJWAL K SAHA2,* 1 Department of Energy and Process Engineering, Norwegian University of Science and Technology, 7491 Trondheim, Norway 2 Department of Mechanical Engineering, Indian Institute of Technology Guwahati, Guwahati 781039, India e-mail: [email protected]; [email protected] MS received 28 August 2020; revised 20 December 2020; accepted 28 January 2021 Abstract. The nozzle forms a large segment of the rocket engine structure, and as a whole, the performance of a rocket largely depends upon its aerodynamic design. The principal parameters in this context are the shape of the nozzle contour and the nozzle area expansion ratio. A careful shaping of the nozzle contour can lead to a high gain in its performance. As a consequence of intensive research, the design and the shape of rocket nozzles have undergone a series of development over the last several decades. The notable among them are conical, bell, plug, expansion-deflection and dual bell nozzles, besides the recently developed multi nozzle grid. However, to the best of authors’ knowledge, no article has reviewed the entire group of nozzles in a systematic and comprehensive manner. This paper aims to review and bring all such development in one single frame. The article mainly focuses on the aerodynamic aspects of all the rocket nozzles developed till date and summarizes the major findings covering their design, development, utilization, benefits and limitations.
    [Show full text]
  • Modelling a Hypersonic Single Expansion Ramp Nozzle of a Hypersonic Aircraft Through Parametric Studies
    energies Article Modelling a Hypersonic Single Expansion Ramp Nozzle of a Hypersonic Aircraft through Parametric Studies Andrew Ridgway, Ashish Alex Sam * and Apostolos Pesyridis College of Engineering, Design and Physical Sciences, Brunel University London, London UB8 3PH, UK; [email protected] (A.R.); [email protected] (A.P.) * Correspondence: [email protected]; Tel.: +44-1895-267-901 Received: 26 September 2018; Accepted: 7 December 2018; Published: 10 December 2018 Abstract: This paper aims to contribute to developing a potential combined cycle air-breathing engine integrated into an aircraft design, capable of performing flight profiles on a commercial scale. This study specifically focuses on the single expansion ramp nozzle (SERN) and aircraft-engine integration with an emphasis on the combined cycle engine integration into the conceptual aircraft design. A parametric study using computational fluid dynamics (CFD) have been employed to analyze the sensitivity of the SERN’s performance parameters with changing geometry and operating conditions. The SERN adapted to the different operating conditions and was able to retain its performance throughout the altitude simulated. The expansion ramp shape, angle, exit area, and cowl shape influenced the thrust substantially. The internal nozzle expansion and expansion ramp had a significant effect on the lift and moment performance. An optimized SERN was assembled into a scramjet and was subject to various nozzle inflow conditions, to which combustion flow from twin strut injectors produced the best thrust performance. Side fence studies observed longer and diverging side fences to produce extra thrust compared to small and straight fences. Keywords: scramjet; single expansion ramp nozzle; hypersonic aircraft; combined cycle engines 1.
    [Show full text]
  • Multidisciplinary Design Project Engineering Dictionary Version 0.0.2
    Multidisciplinary Design Project Engineering Dictionary Version 0.0.2 February 15, 2006 . DRAFT Cambridge-MIT Institute Multidisciplinary Design Project This Dictionary/Glossary of Engineering terms has been compiled to compliment the work developed as part of the Multi-disciplinary Design Project (MDP), which is a programme to develop teaching material and kits to aid the running of mechtronics projects in Universities and Schools. The project is being carried out with support from the Cambridge-MIT Institute undergraduate teaching programe. For more information about the project please visit the MDP website at http://www-mdp.eng.cam.ac.uk or contact Dr. Peter Long Prof. Alex Slocum Cambridge University Engineering Department Massachusetts Institute of Technology Trumpington Street, 77 Massachusetts Ave. Cambridge. Cambridge MA 02139-4307 CB2 1PZ. USA e-mail: [email protected] e-mail: [email protected] tel: +44 (0) 1223 332779 tel: +1 617 253 0012 For information about the CMI initiative please see Cambridge-MIT Institute website :- http://www.cambridge-mit.org CMI CMI, University of Cambridge Massachusetts Institute of Technology 10 Miller’s Yard, 77 Massachusetts Ave. Mill Lane, Cambridge MA 02139-4307 Cambridge. CB2 1RQ. USA tel: +44 (0) 1223 327207 tel. +1 617 253 7732 fax: +44 (0) 1223 765891 fax. +1 617 258 8539 . DRAFT 2 CMI-MDP Programme 1 Introduction This dictionary/glossary has not been developed as a definative work but as a useful reference book for engi- neering students to search when looking for the meaning of a word/phrase. It has been compiled from a number of existing glossaries together with a number of local additions.
    [Show full text]
  • PLUMBING DICTIONARY Sixth Edition
    as to produce smooth threads. 2. An oil or oily preparation used as a cutting fluid espe cially a water-soluble oil (such as a mineral oil containing- a fatty oil) Cut Grooving (cut groov-ing) the process of machining away material, providing a groove into a pipe to allow for a mechani cal coupling to be installed.This process was invented by Victau - lic Corp. in 1925. Cut Grooving is designed for stanard weight- ceives or heavier wall thickness pipe. tetrafluoroethylene (tet-ra-- theseveral lower variouslyterminal, whichshaped re or decalescensecryolite (de-ca-les-cen- ming and flood consisting(cry-o-lite) of sodium-alumi earthfluo-ro-eth-yl-ene) by alternately dam a colorless, thegrooved vapors tools. from 4. anonpressure tool used by se) a decrease in temperaturea mineral nonflammable gas used in mak- metalworkers to shape material thatnum occurs fluoride. while Usedheating for soldermet- ing a stream. See STANK. or the pressure sterilizers, and - spannering heat resistantwrench and(span-ner acid re - conductsto a desired the form vapors. 5. a tooldirectly used al ingthrough copper a rangeand inalloys which when a mixed with phosphoric acid.- wrench)sistant plastics 1. one ofsuch various as teflon. tools to setthe theouter teeth air. of Sometimesaatmosphere circular or exhaust vent. See change in a structure occurs. Also used for soldering alumi forAbbr. tightening, T.F.E. or loosening,chiefly Brit.: orcalled band vapor, saw. steam,6. a tool used to degree of hazard (de-gree stench trap (stench trap) num bronze when mixed with nutsthermal and bolts.expansion 2. (water) straightenLOCAL VENT.
    [Show full text]
  • Scramjet Nozzle Design and Analysis As Applied to a Highly Integrated Hypersonic Research Airplane
    NASA TECHN'ICAL NOTE NASA D-8334 d- . ,d d K a+ 4 c/) 4 z SCRAMJET NOZZLE DESIGN AND ANALYSIS AS APPLIED TO A HIGHLY INTEGRATED HYPERSONIC RESEARCH AIRPLANE Wi'llidm J. Smull, John P. Wehher, and P. J. Johnston i Ldngley Reseurch Center Humpton, Va. 23665 / NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON, D. c. .'NOVEMBER 1976 TECH LIBRARY KAFB, NM I Illill 111 lllll11Il1 lllll lllll lllll IIll ~~ ~~- - 1. Report No. 2. Government Accession No. -. ___r_- --.-= .--. NASA TN D-8334 I ~~ 4. Title and ,Subtitle 5. Report Date November 1976 7. Author(sl 8. Performing Organization Report No. William J. Small, John P. Weidner, L-11003 and P. J. Johnston . ~ ~-.. ~ 10. Work Unit No. 9. Performing Organization Nwne and Address 505-11-31-02 NASA Langley Research Center 11. Contract or Grant No. Hampton, VA 23665 13. Type of Report and Period Covered ,. 12. Sponsoring Agency Name and Address Technical Note National Aeronautics and Space Administration 14. Sponsoring Agency Code Washington, DC 20546 -. I 15. Supplementary Notes -~ 16. Abstract The great potential expected from future air-breathing hypersonic aircraft systems is predicated on the assumption that the propulsion system can be effi- ciently integrated with the airframe. A study of engine-nozzle airframe inte- gration at hypersonic speeds has been conducted by using a high-speed research- aircraft concept as a focus. Recently developed techniques for analysis of scramjet-nozzle exhaust flows provide a realistic analysis of complex forces resulting from the engine-nozzle airframe coupling. Results from these studies show that by properly integrating the engine-nozzle propulsive system with the airframe, efficient, controlled and stable flight results over a wide speed range.
    [Show full text]
  • Rocket Nozzles the Simplest Nozzle Is a Cone with a Half-Opening Angle, Α Attached to a Combustion Chamber (See Figure 3)
    NOZZLES S. R. KULKARNI 1. Motivation In astronomy textbooks it is usually stated that the Bondi-Hoyle solution has a specific value for the accretion rate (given the boundary conditions of ambient density and temper- ature of the gas). Only with this specific accretion rate will there be a seamless transition from sub-sonic inflow to super-sonic inflow. The Bondi-Hoyle or the Parker problem is quite analogous to the rocket problem, in that both involve a smooth transition from sub-sonic to super-sonic flow. What bothered me is the statement in astronomy books that the solution demands a specific accretion (or excretion) mass rate. In contrast, the thrust on a rocket can be varied (as can be gathered if you watch NASA TV). Given the similarity between the astronomical problem and the rocket problem I thought an investigation of the latter may be illuminating and hence this note. 2. The de Laval Nozzle Consider a rocket which is burning fuel. Let M˙ be the burn rate of the fuel and ue be the speed of the exhaust. Then in steady state the vertical “thrust” or force is Mu˙ e. The resulting vertical thrust lifts the rocket. Clearly, it is of greatest advantage to make the exhaust speed as large as possible and to minimize the outflow in directions other than vertical. A rocket engine consists of a chamber in which fuel is burnt connected to a nozzle. A properly designed1 nozzle can convert the hot burnt fuel into supersonic flow (see Figure 1). The integration of the momentum equation (under assumptions of inviscid flow) yields the much celebrated Beronulli’s theorem.
    [Show full text]
  • Glossary of Terms — Page 1 Air Gap: See Backflow Prevention Device
    Glossary of Irrigation Terms Version 7/1/17 Edited by Eugene W. Rochester, CID Certification Consultant This document is in continuing development. You are encouraged to submit definitions along with their source to [email protected]. The terms in this glossary are presented in an effort to provide a foundation for common understanding in communications covering irrigation. The following provides additional information: • Items located within brackets, [ ], indicate the IA-preferred abbreviation or acronym for the term specified. • Items located within braces, { }, indicate quantitative IA-preferred units for the term specified. • General definitions of terms not used in mathematical equations are not flagged in any way. • Three dots (…) at the end of a definition indicate that the definition has been truncated. • Terms with strike-through are non-preferred usage. • References are provided for the convenience of the reader and do not infer original reference. Additional soil science terms may be found at www.soils.org/publications/soils-glossary#. A AC {hertz}: Abbreviation for alternating current. AC pipe: Asbestos-cement pipe was commonly used for buried pipelines. It combines strength with light weight and is immune to rust and corrosion. (James, 1988) (No longer made.) acceleration of gravity. See gravity (acceleration due to). acid precipitation: Atmospheric precipitation that is below pH 7 and is often composed of the hydrolyzed by-products from oxidized halogen, nitrogen, and sulfur substances. (Glossary of Soil Science Terms, 2013) acid soil: Soil with a pH value less than 7.0. (Glossary of Soil Science Terms, 2013) adhesion: Forces of attraction between unlike molecules, e.g. water and solid.
    [Show full text]
  • Design of a Rocket- Based Combined Cycle Engine
    Design of a Rocket- Based Combined Cycle Engine A project present to The Faculty of the Department of Aerospace Engineering San Jose State University in partial fulfillment of the requirements for the degree Master of Science in Aerospace Engineering By Andrew Munoz May 2011 approved by Dr. Periklis Papadopoulos Faculty Advisor © 2011 Andrew Munoz ALL RIGHTS RESERVED 2 3 DESIGN OF A ROCKET-BASED COMBINED CYCLE ENGINE by Andrew Munoz A BST R A C T Current expendable space launch vehicles using conventional all-rocket propulsion systems have virtually reached their performance limits with respect to payload capacity. A promising approach to increase payload capacity and to provide reusability is to utilize airbreathing propulsion systems for a portion of the flight to reduce oxidizer weight and potentially increase payload and structural capacity. A Rocket-Based Combined Cycle (RBCC) engine would be capable of providing transatmospheric flight while increasing propulsion performance by utilizing a rocket integrated airbreathing propulsion system. An analytical model of a Rocket-Based Combined Cycle (RBCC) engine was developed using the stream thrust method as a solution to the governing equations of aerothermodynamics. This analytical model provided the means for calculating the propulsion performance of an ideal RBCC engine over the airbreathing flight regime (Mach 0 to 12) as well as a means of comparison with conventional rocket propulsion systems. The model was developed by choosing the highest performance propulsion cycles for a given flight regime and then integrating them into a single engine which would utilize the same components (inlet, rocket, combustor, and nozzle) throughout the entire airbreathing flight regime.
    [Show full text]
  • Space Shuttle Main Engine Orientation
    BC98-04 Space Transportation System Training Data Space Shuttle Main Engine Orientation June 1998 Use this data for training purposes only Rocketdyne Propulsion & Power BOEING PROPRIETARY FORWARD This manual is the supporting handout material to a lecture presentation on the Space Shuttle Main Engine called the Abbreviated SSME Orientation Course. This course is a technically oriented discussion of the SSME, designed for personnel at any level who support SSME activities directly or indirectly. This manual is updated and improved as necessary by Betty McLaughlin. To request copies, or obtain information on classes, call Lori Circle at Rocketdyne (818) 586-2213 BOEING PROPRIETARY 1684-1a.ppt i BOEING PROPRIETARY TABLE OF CONTENT Acronyms and Abbreviations............................. v Low-Pressure Fuel Turbopump............................ 56 Shuttle Propulsion System................................. 2 HPOTP Pump Section............................................ 60 SSME Introduction............................................... 4 HPOTP Turbine Section......................................... 62 SSME Highlights................................................... 6 HPOTP Shaft Seals................................................. 64 Gimbal Bearing.................................................... 10 HPFTP Pump Section............................................ 68 Flexible Joints...................................................... 14 HPFTP Turbine Section......................................... 70 Powerhead...........................................................
    [Show full text]
  • Comparison of Two Procedures for Predicting Rocket Engine Nozzle Performance
    NASA Technical Memorandum 89814 0-' AIAA-87-207 1 I' t Comparison of Two Procedures for Predicting Rocket Engine Nozzle Performance Kenneth J. Davidian Lewis Research Center Cleveland, Ohio Prepared for the 23rd Joint Propulsion Conference cosponsored by the AIAA, SAE, ASME, and ASEE San Diego, California, June 29-July 2, 1987 COMPARISON OF TWO PROCEDURES FOR PREDICTING ROCKET ENGINE NOZZLE PERFORMANCE Kenneth J. Davidian National Aeronautics and Space Administration Lewis Research Center Cleveland, Ohio 44135 Abstract layer prediction proqram used in this procedure. Unlike BLIMP, BLM is accompanied by a set of sub- Two nozzle performance prediction procedures programs which will calculate all the necessary whicn are based on the standardized JANNAF meth- preliminary information required for the boundary odology are presented and compared for four layer analysis. This total set of subprograms rocket engine nozzles. The first procedure (includinq BLM) is referred to as the 1985 ver- required operator intercedance to transfer data sion of the Two-Dimensional Kinetics program between the individual performance programs. The (TDK.85) .4 second procedure is more automated in that all necessary programs are collected into a single Performance comparisons were made for noz- computer code, thereby eliminating the need for zles having area ratios 60:1, 200:1, 400:1, and data reformatting. Results from both procedures 1OOO:l. Each nozzle had a throat diameter of co Lo show similar trends but quantitative differences. 1 in. and was specified to run at a chamber pres- d P) Agreement was best in the predictions of specific sure of 1000 psia using hydrogen and oxygen as I W impulse and local skin friction coefficient.
    [Show full text]
  • Thrust Augmentation Nozzle (TAN) Concept for Rocket Engine Booster Applications Scott Forde∗, Mel Bulman, Todd Neill
    Acta Astronautica 59 (2006) 271–277 www.elsevier.com/locate/actaastro Thrust augmentation nozzle (TAN) concept for rocket engine booster applications Scott Forde∗, Mel Bulman, Todd Neill Aerojet, Sacramento, CA, USA Abstract Aerojet used the patented thrust augmented nozzle (TAN) concept to validate a unique means of increasing sea-level thrust in a liquid rocket booster engine. We have used knowledge gained from hypersonic Scramjet research to inject propellants into the supersonic region of the rocket engine nozzle to significantly increase sea-level thrust without significantly impacting specific impulse. The TAN concept overcomes conventional engine limitations by injecting propellants and combusting in an annular region in the divergent section of the nozzle. This injection of propellants at moderate pressures allows for obtaining high thrust at takeoff without overexpansion thrust losses. The main chamber is operated at a constant pressure while maintaining a constant head rise and flow rate of the main propellant pumps. Recent hot-fire tests have validated the design approach and thrust augmentation ratios. Calculations of nozzle performance and wall pressures were made using computational fluid dynamics analyses with and without thrust augmentation flow, resulting in good agreement between calculated and measured quantities including augmentation thrust. This paper describes the TAN concept, the test setup, test results, and calculation results. © 2006 Published by Elsevier Ltd. 1. Introduction is less efficient in producing thrust. This is due to the gases over-expanding to a pressure below ambient. This Conventional rocket engines for a launch vehicle results in a portion of the nozzle generating negative booster stage need to deliver high thrust when taking thrust.
    [Show full text]
  • Space Advantage Provided by De-Laval Nozzle and Bell Nozzle Over Venturi
    Proceedings of the World Congress on Engineering 2015 Vol II WCE 2015, July 1 - 3, 2015, London, U.K. Space Advantage Provided by De-Laval Nozzle and Bell Nozzle over Venturi Omkar N. Deshpande, Nitin L. Narappanawar Abstract:-The FSAE guidelines state that it is mandatory for many crucial components are to be fitted in a very little each and every car participating in the said event to have a space. Therefore there is a need to design a new kind of single circular 20mm restrictor in the intake system. All the air nozzle achieving optimality at a higher angle than that of the flowing to the engine must pass through this restrictor. Conventionally, a Venturi Nozzle is used as a restrictor. In our venturi nozzle. For this purpose De Laval Nozzle and Bell research, we have proposed two Nozzles: De-Laval Nozzle and Nozzle are analyzed as a possible alternative to the venturi. Bell Nozzle as an alternative to the Venturi Nozzle. After De- Laval Nozzle is used in certain type of steam turbines numerous CFD Simulations; we have inferred that the results and also as a Rocket Engine Nozzle [6]. Bell Nozzle is also of the De-Laval Nozzle and Bell Nozzle are similar to the widely used as a Rocket Engine Nozzle. Both of the nozzles Venturi Nozzle. Along with providing similar results, the two achieve optimality at a higher angle of convergence as nozzles provide a space saving of 6.86% over the Venturi Nozzle. The data was gathered from SolidWorks Flow demonstrated in ‘Section V parts A.); B.).’ Simulation 2014.
    [Show full text]