U.S. patent number 3,670,994 [Application Number 05/063,369] was granted by the patent office on 1972-06-20 for variable deflection thrusters for jets.
This patent grant is currently assigned to The United States of America as represented by the Secretary of the Navy. Invention is credited to Apostolos P. Kizilos.
United States Patent |
3,670,994 |
Kizilos |
June 20, 1972 |
VARIABLE DEFLECTION THRUSTERS FOR JETS
Abstract
Variable deflection thrusters center body of improved design for
jets for ercoming stream detachment at high mach numbers and high
pressure ratios.
Inventors: |
Kizilos; Apostolos P.
(Minnetonka, MN) |
Assignee: |
The United States of America as
represented by the Secretary of the Navy (N/A)
|
Family
ID: |
22048731 |
Appl.
No.: |
05/063,369 |
Filed: |
August 13, 1970 |
Current U.S.
Class: |
244/207; 416/20R;
416/90A |
Current CPC
Class: |
B64C
9/38 (20130101) |
Current International
Class: |
B64C
9/38 (20060101); B64C 9/00 (20060101); B64c
021/04 () |
Field of
Search: |
;244/42R,42CD,42CC,42C,40,41 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Buchler; Milton
Assistant Examiner: Rutledge; Carl A.
Claims
What is claimed is:
1. An improved variable deflection thruster at the rearward end of
an airfoil for use at high subsonic speeds without jet detachment,
comprising:
a. an airfoil having opposite first and second side surfaces
substantially merging at the rearward end of the airfoil into a
sharp trailing edge,
b. said rearward sharp trailing edge being formed from one side
edge of a biconvex centerbody,
c. first and second spanwise-extending jet discharge apertures in
said airfoil, one said jet discharge aperture being on each side of
said biconvex centerbody which forms said trailing edge,
d. each of said first and second jet discharge apertures being
shaped and arranged to discharge a fluid stream as a layer
rearwardly over the surfaces of said biconvex centerbody,
e. first and second jet pressure supply and control means to
provide a fluid jet stream from each said first and second jet
discharge apertures, respectively, and to vary the flow of said jet
streams discharged from said apertures relative to one another.
2. An improved variable deflection thruster at the rearward end of
an airfoil for use at high transonic and supersonic speeds without
jet detachment, comprising:
a. an airfoil having opposite first and second side surfaces
substantially merging at the rearward end of the airfoil into a
wedge shaped trailing edge,
b. said rearward wedge shaped trailing edge being formed by a
variable deflection thruster centerbody having two flat sides which
intersect to form a wedge,
c. first and second spanwise-extending jet discharge apertures in
said airfoil, one said jet discharge aperture being on each side of
said variable deflection thruster centerbody having two flat sides
which intersect to form said wedge shaped trailing edge,
d. each of said first and second jet discharge apertures being
shaped and arranged to discharge a fluid stream as a layer
rearwardly over the flat surfaces of said variable deflection
thruster centerbody,
e. first and second jet pressure supply and control means to
provide a fluid jet stream from each said first and second jet
discharge apertures, respectively, and to vary the flow of said jet
streams discharged from said apertures relative to one another.
Description
The invention herein described may be manufactured and used by or
for the Government of the United States of America for governmental
purposes without the payment of any royalties thereon or
therefor.
The basic variable deflection thruster (VDT) concept is disclosed
by Davidson U.S. Pat. No. 3,062,483 and comprises a curved
two-dimensional surface and two nozzles for directing fluid streams
tangent to the surface. The streams attach to the surface due to
the Coanda effect, and flow around the surface to impinge on each
other to form one stream which then exits from the surface in a
direction determined by the relative momenta of the original two
streams. The net effect is a fluid stream whose direction and
strength can be varied by fluid means without the use of mechanical
swivels, etc.. Attachment, also called the Coanda effect, is
essential for the operation of the VDT, and was first described by
Coanda in U.S. Pat. No. 2,052,869. It depends upon entrainment of
flow along the jet, depletion of the ambient fluid between the jet
and the attachment wall, and subsequent pressure differential
across the jet which is directly responsible for the
attachment.
However, when the momentum of the jet is too great and the radius
of curvature too small, the stream will not attach, but will flow
straight past the curved surface. It is this problem which is
encountered with conventional VDT's using circular cross-sectioned
surfaces shown in FIG. 1. The present invention overcomes this
problem with the biconvex VDT and straight edge VDT disclosed
herein. A VDT surface shaped like a football cross-section has been
found to overcome stream detachment at high mach numbers and high
pressure ratios.
Other objects and many of the attendant advantages of this
invention will become readily appreciated as the same becomes
better understood by reference to the following detailed
description when considered in connection with the accompanying
drawings wherein:
FIG. 1 shows a conventional VDT design.
FIG. 2 shows pressure ratio vs. nozzle and VDT dimensions.
FIG. 3 shows a preferred embodiment of the invention using a
biconvex VDT center body.
FIG. 4 shows a straight edge VDT center body.
The conventional VDT basic configuration shown in FIG. 1 consists
of a cylindrical surface 10 on which two jets, issuing from
diametrically opposed spanwise-extending discharge apertures or
nozzles 11 and 12, attach. The two jets meet on the surface of
cylinder 10 at a position determined by their pressure difference.
The jets subsequently form a single combined jet 14 which leaves
cylinder surface 10 at some predetermined angle. The exiting angle
of the combined jet 14 changes as a result of the bending imposed
by the unequal static pressures of the two half-jets.
It is essential in the operation of this VDT configuration (which
allows maximum jet deflection) that the two half-jets remain
attached to the cylinder surface. Each one of these jets clings to
the cylinder surface 10 by virtue of the Coanda effect. The limits
of jet attachment are determined by the jet pressure and the
geometry of the configuration. Large slots or nozzles, large
pressures, and small-diameter Coanda cylinders tend to cause jet
detachment.
Because of the importance of jet detachment upon VDT operation,
tests were undertaken to determine the flow and geometrical
parameters which control the detachment of a single Coanda jet. The
VDT jet detaches when for a given geometry the pressure ratio of
the jets is increased beyond a given value, thus spoiling the VDT
effect. For a fixed nozzle width "b", the greater the radius "a" of
cylinder 10 the higher the pressure ratio that the jet can support
before it detaches, see FIG. 2.
When the thickness "t" of an airfoil 15 is limited it has been
found that a biconvex VDT can be used as shown in FIG. 3 to support
a higher pressure ratio jet from apertures 11 and 12 than would be
otherwise possible. This biconvex centerbody 16 forms a sharp
trailing edge which overcomes the stream detachment occurring with
a cylindrical VDT at high mach numbers and high pressure ratios.
The biconvex VDT 16 is attached to plate 18 that separates the two
plenum chambers within the airfoil 15, from which the high pressure
jets are supplied. Jet pressure supply is provided to the plenum
chambers on either side of plate 18. Jet pressure supplies 20 and
21 are controlled to vary the flow of the jet streams from
apertures 11 and 12 relative to each other.
A variable deflection thruster center body 17 having two flat sides
19 which intersect to form a wedge can also be used to solve the
stream detachment problems encountered with the conventional
circular VDT surface. The attached jets do not operate on the
Coanda effect but rather follow the straight edges of the center
body 17. The straight walls 19 of this embodiment shown in FIG. 4
are a limiting case of increasing the radius of curvature until a
straight line is approached. The two jets of the straight edge VDT
flow along the walls to meet with a pure momentum interchange type
of stream interaction.
The Coanda effect is not present when a jet is flowing along side a
flat surface. Either a curved surface, or a "recess" or "offset"
such as is employed in the nozzle and interaction region of a fluid
amplifier, is necessary for the Coanda effect. That is, there must
be a "bubble" from which depletion of fluid occurs so as to
generate a pressure differential. In the embodiment of FIG. 4, the
Coanda effect is not present, and operation of the invention
depends upon stream interaction, also known as momentum
interchange. In conventional curved surface VDTs both the Coanda
effect and the momentum interchange effects are utilized. Both the
biconvex design of FIG. 3 and straight edge design of FIG. 4 form a
sharp wedge where the sides come together eliminating problems
encountered with a conventional circular VDT surface.
The biconvex VDT device has good lift-production capability up to
mach number 0.5. The VDT configuration with straight surfaces (FIG.
4) can eliminate jet detachment problems at high transonic and
supersonic speeds.
* * * * *