Pulse Detonation Propulsion Options

PDE Options: From Air Breathing to Rocket Propulsion
Aerospace Engineering Consulting
Arlington, TX
Dora Musielak, Ph.D.
All rights reserved. No part of this publication may be reproduced, distributed, or transmitted, unless for course participation, in any form
or by any means, or stored in a database or retrieval system, without the prior written permission of the Author. Contact D. Musielak
dmusielak@uta.edu

• Overview of CPC and CVC Options
• Constant Volume Combustion
(CVC)
• Hybrid Jet Engines
• PDRE
• Hybrid Propulsion for Space Planes
• Continuous Detonation Wave
Engine (CDWE)
• Rotating Detonation Engine (RDE)
• Pressure Gain Cycle (PGC)
• Pulsejet as PGC
PDE Propulsion Options
AIAA Pulse Detonation Engine Technology – D. Musielak
2

CPC and CVC Cycle Concepts
Air Breathing
(Brayton Cycle)
Rockets
(Brayton Cycle)
Detonation Engines
(Humphrey Cycle)
Gas Turbine Engines No Rotor Engines
Turbo-
fan
Turbo-
jet
Pulse-
jet
Ram and
Scramjet
All
Rockets
AB PDE PDRE
Turbofan
+ AB
Turbojet +
AB
Hybrid Cycle Engine Hybrid Cycle Engine
Turbofan +
Ramjet
Turbojet +
Ramjet
Turbo-
Rocket
Ram-
Rocket
Rocket-
Scramjet
Turbofan-
PDE
PDE-
Ramjet
PDE-
Scramjet-
Rocket
3

Detonation for PropulsionDetonationwave(DW)
propagationtocreatethrust
Oblique Detonation Wave Engine (ODWE)
• Combustible gas mixture injection velocity equals or exceeds detonation
Chapman-Jouguet (CJ) velocity.
• Detonation waves (DWs) or oblique detonation waves (ODWs) are positioned to
combust injected combustible mixture.
Pulse Detonation Engine (PDE)
• Cyclically detonates fuel and atmospheric air mixtures to generate thrust.
•  PDE differs from conventional propulsion systems in two primary ways:
generates thrust intermittently, and produces a high pressure rise in combustor.
• Detonation-generated pressure rise represents primary benefits of a PDE: it
may reduce engine compression requirements.
Continuous Detonation Engine (CDE)
• Combustible gas mixture is injected along axial direction, and DWs propagate in
azimuthal direction.
• Two directions are independent, DWs can continuously propagate with range of
combustible gas injection velocities and do not require multi-time ignition.
4

Pure PDE Cycle
1: Fuel-Oxidizer
Injected and
Mixed
2: Detonation
Initiated
3: Detonation
wave moves
through gas
mixture
4: High
pressure gas
fills detonation
chamber
5: Detonation wave exits
chamber and air is drawn
in by reduced pressure
Thrust is directly proportional to detonation frequency
FILL DETONATE
EXHAUST
Repeat
5

Constant Volume Combustion (CVC) Cycle
•  Engines operating on constant–volume cycle (CVC) offer a
means of improving performance of jet propulsion.
•  CVC possesses theoretical advantages over constant-pressure
cycle including higher ideal efficiency and output per pound of
air handled per unit time.
•  Actual performance of a CVC jet engine depends upon extent to
which constant-volume combustion is approached and resulting
pressure developed in combustion chamber.
Can we augment gas turbine performance with PDEs
or any other form of constant volume combustion
(CVC) cycle to extend supersonic flight regime?
6

PDE as CVC in Turbine
PDE as mixed flow afterburner
PDE as combustor PDE as afterburner
Possible configurations may require multi-tube PDEs
7

Hybrid PDE-Turbine Engine
•  A hybrid turbofan-PDE would combine both systems: central core
engine would still turn large fan in front, but bypass would flow into a
ring of PDEs.
•  Hybrid turbofan-PDE system would produce significantly more thrust
without requiring additional fuel.
8

A Turbofan augmented with PDE?
PDE
PDE
PDE
9
Pulse detonation augmenter replaces core of turbofan (GE Patent 6550235)

A Turbofan augmented with PDE
10
• Rasheed et al. tested multitube PDC with
eight tubes arranged in a can-annular
configuration integrated with a single-stage
axial turbine nominally rated for 10 lbm/s,
25,000 rpm, and 1000 hp.
• High frequency pressure transducers
installed revealed complex wave
interactions with significant downstream
tube-to-tube interactions affecting
operability when using sequential firing
pattern.
• Study suggests that noise may not be a
significant barrier to commercial
applications of PDC-turbine hybrid engines
J. Propulsion & Power (2009)

GE GR Hybrid PDC-Turbine
M. Baptista,A. Rasheed, , et al., AIAA 2006-1234
• An 8-tube, can-annular multi-tube PDE operated in several firing patterns
using stoichiometric C2H4-air detonations.
• Turbine mechanical response measurements made with strain gages
operating system for over 5 minutes, allowing rig to achieve thermal steady
state conditions to characterize mechanical response of turbine stator
11
292 mm circle
PDC length: 1.5 m

GE GR Hybrid PDC-Turbine
A. Rasheed, , et al., J. P&P (2009)
12
• Each 49.3 mm (1.939 in.) diameter tube has 800.1 mm (31.5 in) length
measured from downstream face of fuel–air mixing element to tube exit.
• Length represents distance in which C2H4-air detonation is achieved.
• Spark plug mounted ~ one diameter downstream of fuel–air mixing element to
allow mixing before detonation initiated

PDE in Bypass Duct of Turbofan
Ref: Mawid, et al., Application of PDC to Turbofan Engines, J. Eng. Gas Turbines and Power (2003)
13
• Thrust, SFC and specific thrust of conventional afterburner turbofan and pulse
detonation turbofan engine concept were calculated and compared, using
multidimensional CFD analysis.
• Results showed significant performance gain can be obtained using PD
turbofan engine as compared to AB turbofan engine.
• Demonstrated that for a PD bypass duct operating at 100 Hz or higher, thrust,
SFC and specific thrust of PD turbofan can nearly be twice as much as those of
conventional AB turbofan engine.
• Effects of fuel-air mixture equivalence ratio and partial filling on performance
were also predicted.

PDE in Bypass Duct of Turbofan
Ref: Mawid, et al., Application of PDC to Turbofan Engines, J. Eng. Gas Turbines and Power (2003)
14

PDE better than Ramjet
•  System-level performance analyses of PDE, based on specific impulse,
compared to that of a ramjet Mach 1.2 to 3.5.
•  Using a constant-volume analytical model, event timing, geometric and
injection parameters providing optimal performance were determined. These
were then used as input to a one-dimensional model, based on method of
characteristics, and a two-dimensional model, based on CFD.
•  Effect of partial fill and nozzle expansion ratio on Isp was also evaluated.
•  For all models and over range of Mach numbers considered, PDE’s Isp was
consistently greater than that of a ramjet.
•  Partial fill and nozzle expansion ratio were also identified as important factors
influencing performance.
Harris, et. al., Pulse detonation engine as a ramjet replacement, J. of Propulsion and Power, 2006, vol. 22,
no2, pp. 462-473
15

PDE better than Turbo-Ramjet
•  Study screened a large matrix of possible applications for advanced design
analysis è best suited to PDE:
–  supersonic tactical aircraft,
–  a supersonic strike missile, and
–  hypersonic single-stage-to-orbit (SSTO) vehicle.
•  Supersonic tactical aircraft was focus of paper, envisioned as a Mach 3.5
high-altitude reconnaissance aircraft with possible strike capability.
•  Relative to a turbo-ramjet powered vehicle, study identified an 11% to 21%
takeoff gross weight (TOGW) benefit on baseline 700 n.mi. radius mission.
•  TOGW benefits predicted resulted from PDE lower cruise SFC and lower
vehicle supersonic drag. Lower vehicle drag resulted from better aft vehicle
shaping, which was a result of better distribution of the PDE cross-sectional
area.
•  Reduction in TOGW and fuel usage produced an estimated 4% reduction in
life cycle cost for the PDE vehicle.
Ref: Kaemming, T., Integrated Vehicle Comparison of Turbo-Ramjet Engine and Pulsed Detonation Engine
J. Eng. Gas Turbines Power -- January 2003 16

Turbo-ramjet vs PDE Comparison
Ref: Kaemming, T., Integrated Vehicle Comparison of Turbo-ramjet engine and PDE (2001-GT-451)
17

Pulse Detonation Rocket Engine (PDRE)
•  PDREs use fuel and oxidant carried
onboard a flying vehicle.
•  Pulse detonation technology can in
principle be applied to PDREs.
•  Bussing patented in 1999 a PDRE with
six cylindrical DCs each having inlet
end and outlet end.
•  Outlet ends are in fluid communication
with nozzle that directs thrust vector
produced from detonation products
expelled from chambers.
18

Todorki Japan’s PDRE
Ref: Kashara, et al. J. P&P (2009)
19
Stability of PDRE operation depends
on ratio between purge-gas thickness
and tube diameter.

Kashara, et al. PDRE (2009)
20

A PDE Rocket Plane to Space?
21
Ref: Ulf Olsson, Aerospace Propulsion – Stockholm (2006)

PDREs for Spaceplanes
•  There are various ways of incorporating pulse detonation devices
into a propulsion system, with much interest centering on space
access.
•  J.-L. Cambier: Preliminary modeling of pulse detonation rocket
engines. AIAA 99-2659 (1999)
•  D. Mueller, T. Bratkovich, K. Lupkes, S. Henderson, J. Williams, T.
Bussing: Recent ASI progress in pulse detonation rocket engine
hardware development. AIAA 99-2886 (1999)
•  P.A. Czysz, C.P. Rahaim: `Comparison of SSTO launchers powered
by an RBCC propulsion system and a pulse detonation wave
propulsion system'. In: Proc 6th Int Symp Propulsion Space
Transportation XXIst Century, Versailles, May 1416, 2002, Paper
S19-2
•  F. Lu and D. Wilson, Some perspectives on pulse detonation
propulsion systems, 1051-ISSW24 (University of Texas – Arlington)
22

PDR-based Single-Path, Multi-Mode Spaceplane
1.  An ejector-augmented PDR for
take off to moderate supersonic
Mach
2.  A pulsed normal detonation wave
mode at combustion chamber
Mach number Mcc < MCJ
3.  An oblique detonation wave mode
of operation when Mcc > MCJ
4.  A pure PDR mode of operation at
high altitude.
Ref: F. Lu and D. Wilson (2004)
23

UTA Spaceplane Patent
US Patent 6857261 – Wilson and Lu (2005) 24

Continuous Detonation Wave Engine (CDWE)
•  B.V. Voitsekhovskii proposed in 1959
alternative method to realize continuous
detonation.
•  He used analogy with process of running wave
occurring in case of spin-detonation propagation
in a round tube. In both cases burning of
mixture is achieved in a transversal detonation
wave (TDW) moving normally from main
direction of combustion products.
Ref. Falempin (2008) RTO-EN-AVT-150
During ordinary spin detonation,
transversal detonation wave
propagates along forward shock
front in a spiraling trajectory
relatively to tube and burns a
shock-compressed mixture.
25
Continuous Detonation Wave Engine
(CDWE): a CDE with a generally annular
combustion chamber dimensioned to allow
a fuel mixture to detonate continuously.

CDWE
•  Main feature of CDWE is an annular combustion chamber closed on
one side (where fuel injection takes place) and opened at other end.
•  Inside chamber, one or more detonation waves propagate normal to
direction of injection.
•  CDWE is close to an infinite number of small PDEs globally running at
high frequency (several kHz) and dephased, so mean pressure inside
chamber is higher than for a typical PDE.
Falempin, F. (2008) Continuous Detonation Wave Engine. In Advances
on Propulsion Technology for High-Speed Aircraft (pp. 8-1 – 8-16).
MBDA France designed an actual size CDWE
demonstration engine to be manufactured and
tested in next years.
Actively-cooled combustion chamber is 350 mm
(external inner diameter) and 280 mm (internal
inner diameter) and will operate with GH2 / GO2
or GH2 / LO2.
26

CDWRE
•  CDWE rocket mode (CDWRE) for which continuous detonation
process can lead to a compact and very efficient system enabling
lower feeding pressure and thrust vectoring with integration capability
for axi-symmetrical vehicles.
•  CDWE could also be applied to simplified Ramjet Engine with short
ram-combustor and possible operating from Mach 0+ without integral
booster or to Turbojet with improved performances or simplified
compression system (lower compression ratio required).
•  Wolanski , Bykovskii, et al., and Daniau et al. are among researchers
studying Rotating Detonation Engines (RDEs) and considering
applications of RDEs in turbojet, ramjet, and rocket propulsion.
Falempin, F. (2008) Continuous Detonation Wave Engine. In Advances on Propulsion Technology for High-Speed Aircraft.
27

Rotating Detonation Engine (RDE)
•  Rotating Detonation Engine (RDE) is a form of CDE propulsion
concept that involves a continuous detonation process, i.e., not
pulsed, and for which only one detonation initiation is required.
•  In a Rotating Detonation Engine (RDE) a combustible gas mixture is
injected along the axial direction, but DWs propagate in azimuthal
direction.
•  Because two directions are independent, detonation waves can
continuously propagate with a wide range of combustible gas
injection velocities and do not naturally require multi-time ignition.
•  In recent years, RDEs extensively studied experimentally by
Bykovskii et al. (2006). Their experiments achieved both liquid and
gas fuel detonation in combustors with different shapes and with
supersonic or subsonic injection flow.
•  Kindracki et al.(2009) experimentally achieved significant propulsive
performance from an RDE.
28

RDE
29Ref: Toshi Fujiwara, FF Laboratory, Nagoya (Japan)
RDE uses a detonation wave rotating in a toroidal area in a coaxial cylinder

RDE Principle of Operation
•  Principle of RDE based on creation of high centrifugal force,
resulting from a detonation propagating in a disk-like combustion
chamber (toroidal or ring-like shape).
•  In a typical detonation, flow velocity immediately behind CJ point is
equal to about ½ of CJ propagation velocity, which is highly
supersonic. Thus, after detonation has propagated in toroidal
chamber, burnt products of detonation will be subjected to a strong
centrifugal force and be forced to approach outer wall of chamber,
creating a significant pressure/density gradient across radial
direction.
•  Because if this pressure gradient (low pressure on inner wall), low
pressure over inner wall will stimulate self-sustaining (sucking)
supply of fresh mixture into combustion chamber.
30
Ref: Wolanski, et al.

RDE 3-D Simulations
•  Numerical simulation based on a one-step chemical reaction model
to investigate changes in mode of H2-Air detonation wave
propagation from rotating detonation wave (RDW) mode to
standing detonation wave mode.
•  Physical characteristics of RDW with injection velocity of 500 m/s
were analyzed to investigate physical mechanisms involved.
•  With increasing injection velocity, detonation wave gradually
changes from perpendicular to head wall to parallel to head wall.
•  When injection velocity exceeds Chapman–Jouguet velocity 𝑉CJ (~
1984 m/s), detonation wave changes orientation to become
perpendicular to fuel injection direction, and rotating mode changes
accordingly to standing mode.
31Ref: Shao, et al., CHIN. PHYS. LETT. Vol. 27, No. 3 (2010) 034705

Continuous Detonation Propulsion
http://arc.uta.edu/research/cde.htm
First RDWE during beginning
of testing where ignition
sequencing is critical
First RDWE towards end of a test
where burning is deflagration
RDWE at UTA was able to produce a rotating
wave although only for a few rotations
New RDWE version uses hydrogen and air/oxygen to initiate the
detonation wave in annular chamber. Smaller and lighter, new
RDWE uses fuel/oxidizer premixing with new injection approach.
It is currently awaiting thrust stand testing.
32

Wave Rotor as Pressure Gain Combustor
•  Wave rotor technology offers a method of sequencing non-steady
confined combustion in multiple chambers to generate pressure gain
with relatively steady inflow and outflow suitable for integration with
inlets, nozzles, or turbomachinery.
Ref: Akbari and Nalim, J. P&P, Vol. 25 (2009) 33

Pulsejet
• Deflagration Combustion occurs in pulses.
• Few or no moving parts, and capable of running statically.
•A Valveless pulse jet does not require forward motion to run
continuously and are low in cost, lightweight
34

PGC and Pulsejets
Pressure gain combustion
(PGC): method to increase
pressure across combustion
chamber, resulting in higher
efficiency engines.
PGC can be achieved via a
high frequency, resonant,
pulsed combustion process
such as that in pulsejets.
35

Summary
•  Numerous engine concepts that rely on detonation
combustion have been studied and evaluated at
preliminary design level, for both space launcher and
missile applications.
•  Some advances made to date è must prove that
advantages of PDE/PDRE and hybrid turbine/PDE
concepts are not superseded by difficulties to design real
engine and integrate it with an operational vehicle.
•  Controlling detonation to generate thrust can be
challenging!
•  Need to understand physics of detonation combustion,
and get a strong theoretical foundation to develop this
promising propulsion technology.
36

References
•  Kailasanath, K., “Review of Propulsion Applications of Detonation
Waves,” AIAA Journal, Vol. 38, No. 9, 2000, pp. 1698–1708.
•  Kailasanath, K., “Recent Developments in the Research on Pulse
Detonation Engines,” AIAA Journal,Vol. 41, No. 2, 2003, pp. 145–
159.
•  Bazhenova, T. V., and Golub, V. V., “Use of Gas Detonation in a
Controlled Frequency Mode (Review),” Combustion, Explosion, and
Shock Waves, Vol. 39, No. 4, 2003, pp. 365–381.
•  Roy, G. D., Frolov, S. M., Borisov, A. A., and Netzer, D. W., “Pulse
Detonation Propulsion: Challenges, Current Status, and Future
Perspective,” Progress in Energy and Combustion Science, Vol. 30,
No. 6, 2004, pp. 545–672.
•  Kasahara, J., Hasegawa, A., Nemoto, T., Yamaguchi, H.,Yajima, T.,
and Kojima, T., Performance Validation of a Single-Tube Pulse
Detonation Rocket System, J. of Propulsion and Power, Vol.
25(2009), pp.173-180.
37

References
•  Schauer, F., Stutrud, J., and Bradley, R., Detonation initiation studies
and performance results for pulsed detonation engine, AIAA Paper
2001-1129 (2001).
•  Talley, D. G., and Coy E. B., Constant volume limit of pulsed
propulsion for a constant ideal gas, J. Propulsion and Power, Vol. 18
(2002), pp.400-406.
•  Harris, P. G., Stowe, R. A. Ripley, R. C., and Guzik, S. M., Pulse
detonation engine as a ramjet replacement, J. Propulsion and Power,
Vol.22 (2006), pp.462-473.
•  Ma, F., Choi, J.-Y., and Yang, V., Propulsive performance of
airbreathing pulse detonation engines, J. Propulsion and Power, Vol.22
(2006), pp.1188-1203.
•  Kasahara, J., Hirano, M., Matsuo, A., Daimon, Y., and Endo, T., Thrust
Measurement of a Multi-Cycle Partially Filled Pulse Detonation Rocket
Engine, J. of Propulsion and Power, Vol.25(2009), pp.1281-1290.
38

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