Henderson, Brenda

Simmons, Shaun P.

NASA Technical Reports Server

Fundamental Aeronautics Program 
High Speed Project 
National Aeronautics and Space Administration 
Three-Stream Jet Test Plans 
Brenda Henderson, NASA Glenn Research Center 
 
Acoustics Technical Working Group 
April 23 – 24, 2013 
Cleveland, Ohio 
www.nasa.gov 
https://ntrs.nasa.gov/search.jsp?R=20150009541 2019-08-31T10:31:37+00:00Z
Objectives of Study 
• Develop baseline for future third-stream concepts 
• Determine noise reduction potential of “stair-
stepping” velocity 
• Guide future third-stream designs 
– Offset stream concepts 
– Ejectors 
– Inverted velocity concepts 
• Develop prediction tools for three-stream jets 
Previous Three-Stream Investigation 
90o 150
o 
NTRc = 3.2 
Simulated 2-Stream Jet, BPRfan/core = 4.7 
Simulated 2-Stream Jet, BPRfan/core = 6.3 
3 
NPRc NPRb NPRt 
Core 
Fan 
Third Stream 
Ab/Ac = 2.82 
At/Ac = 0.56 
NPR = Nozzle Pressure Ratio 
NTR = Nozzle Temperature Ratio 
Plan for 2014 Study 
• Study will use a three-stream, externally mixed, 
convergent nozzle system 
• Existing core nozzles will be used  
• Core and fan streams will be subsonic 
• Third stream will include subsonic and supersonic 
operating conditions 
• Study will investigate the impact of area ratios and 
operating conditions on resulting far-field acoustics 
Existing Dual-Stream Nozzle System 
Internally Plugged 
Externally Plugged 
• Core-nozzle trailing edges 
and plugs are replaced to go 
from externally plugged to 
internally plugged 
• Dual-stream nozzle system 
mounts on externally mixed 
model 
• Three-stream model required 
for current experiments 
mandates the manufacture of 
new fan nozzles 
 Use existing core internally and 
externally plugged trailing edge pieces 
and plugs 
 Manufacture new fan and third-stream 
trailing edge pieces 
 Baseline (no flow) nozzle for third stream 
 Operating conditions of interest 
- 2.5 < BPRtot< 5.5 
 BPRtot = (fan+third)/core 
- 1.5 < NPRf,c < 1.8 
- 1.3 < NPRt < 2.4 
- 1.0 < NTRc < 3.2 
- NTRf = NTRt = 1.25 
- Range of area ratios 
Target Investigation 
Retain Core Nozzle 
Trailing Edge and Plug 
Manufacture  
• Two core-nozzle 
entrance sections 
• One  and fan-nozzle 
trailing edge 
• Three third-stream 
nozzles 
Proposed Experiments 
7 
0
0.2
0.4
0.6
0.8
1
1.2
0 0.5 1 1.5 2 2.5 3
A
t/
A
c
 
Ab/Ac 
(1.00, 0.60) (2.50, 0.60) (1.75, 0.60) 
(1.75, 0.80) (1.00, 0.80) 
(1.00, 1.00) 
(1.75, 1.00) 
(2.50, 0.80) 
(2.50, 1.00) 
Area Ratios from 
Previous Test 0.6 < Ub/Uc < 1 
0.6 < Ut/Ub < 1.2 
1.0 < Tc/Ta < 3.2 
Proposed Model 
• Base on approach developed by Fisher et al. for dual-stream jets (Fisher, 
Preston, Bryce, AIAA-1993-4413 and Fisher, Preston, Mead, AIAA-1996- 
1666) 
• Model will benefit from PIV measurements 
Primary 
Initial Region Transition Region Fully Mixed Region 
Vs, Ts, Ds Vp, Tp, De Vm, Tm, Dm 
Status 
• Core and fan nozzle flow lines 
complete 
• Preliminary CFD complete 
U/Ujet 
Ab/Ac = 1.0 
At/Ac = 1.0 
Ab/Ac = 1.75 
At/Ac = 1.0 
Ab/Ac = 2.5 
At/Ac = 1.0 
TKE 
Equal Thrust 
Dual Stream Jet 
Three-Stream Jet 
Next Steps 
• Complete co-annular nozzle-system RANS 
solutions for all area ratios and use JENO to predict  
far-field noise 
• Design and manufacture hardware 
• Conduct RANS investigations of offset stream 
concepts 
• Conduct RANS investigations for ejector concepts 
• Complete noise experiments for co-annular and 
possibly offset stream concepts – Feb. 2014  
• Complete follow-on PIV experiments – Spring 2014 
 


Three-Stream Jet Test Plans

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