US3005309A

US3005309A - Streamlined ring for assuring optimum compression in a ramjet

Info

Publication number: US3005309A
Application number: US320896A
Authority: US
Inventors: Randolph S Rae
Original assignee: Individual
Current assignee: Individual
Priority date: 1952-11-17
Filing date: 1952-11-17
Publication date: 1961-10-24
Anticipated expiration: 1978-10-24

Description

Oct. 24, 1961 Filed Nov. 1'7, 1952 R. S. RAE STREAMLINED RING FOR ASSURING OPTIMUM 2 Sheets-Sheet 1 COMPRESSION IN A RAMJET INVENTOR RANDOLPH S. RAE

ATTORNEYS l Oct. 24, 1961 R. s. RAE 3,005,309

STREAMLINED RING FOR ASSURING OPTIMUM COMPRESSION IN A RAMJET Filed Nov. 17. 1952 2 Sheets-Sheet 2 RANDOLPH S. RAE

ATTORNEYS INVENTOR 3,005,309 STREAMLINED RlNG FOR ASSURING OPTIMUM COMPRESSION IN A RAMJET Randolph S. Rae, Silver Spring, Md, assignor to the United States of America as represented by the Secretary of the Navy Filed Nov. 17, 1952, Ser. No. 320,896 9 Claims. (Cl. 60-356) The present invention relates to aerial missiles and more particularly to air inlets for ramjet missiles. This application is a continuation-in-part of the co-pending application entitled Streamlined Rings for Assuring Isentropic Compression of Supersonic Stream Through a Conventional Missile Diffuser, Serial Number 127,727, Randolph S. Rae, inventor, filed, November 16, 1949 now Patent No. 2,975,587.

The supersonic ramjet inlets now in use, such as the Oswatitsch diffuser, the multiple shock diffuser, and the wing scoop diffuser, have certain inherent defects which detract from their efiicient operation. Primarily, in order to attain the fullest isentropic compression possible with an Oswatitsch diffuser, the cowling lip must be disposed at an angle which permits the incoming air to be decelerated smoothly and gradually. This angle is so large that, because of structural considerations, a large surface area is presented to the air stream. As a result, a strong spurious shock wave is formed in front of the lip. Inasmuch as the beneficial weak shock waves produced by the center body of the diffuser are normally all focused upon the lip, the strong spurious shock wave interferes to upset the optimum pattern of the beneficial weak shock waves. This condition is responsible for low. compression and the inefficient operation of the diffuser.

A second defect involves an increase in drag forces caused by the large surface area of the lip facing the air stream. High drag forces are undesirable in that they reduce the useful thrust obtainable from the ramjet.

The invention of the. above-identified application from which the present application is a continuation-in-part, overcomes these defects by positioning a streamlined ring in front of the cowling lip. In this manner the strong spurious shock wave is eliminated from the region proximate to the lip, thus eliminating interference with the shock wave pattern produced by the center body. In addition, the drag forces are reduced because of the streamlined configuration of the ring, which, in effect, diverts the air stream to either side of the diffuser cowling.

However, while the efliciencies obtained by the use of streamlined rings in accordance with the above-mentioned original application were high, they were not as high as could be expected. It was foundthat the high pressures existing in the slot between the diffuser lip and the streamlined ring, as a result of spill-over, caused the boundary layer of relatively dead air to separate from the inner surface of the ring. The separated boundary layer interacted with the shock wave pattern at the inlet, thus preventing the fullest possible isentr'opic compression.

It is therefore an object of this invention to provide a ramjet diffuser inlet which prevents the interference of separated boundary layers with optimum compression, thereby increasing the efficiency of compression.

Another object of the present invention is to provide a ramjet diffuser inlet having a minimum amount of aerodynamic drag and being capable of producing a compression of a supersonic stream approaching isentropic values.

Other objects and many of the attendant advantages of the invention will be readily appreciated as the same Patented Oct. 24, 1961 ice becomes understood by reference to the following detailed description, when considered in connection with the accompanying drawings, wherein:

FIG. 1 is an axial section, partly in elevation, through the forward end portion of a ramjet, illustrating an embodiment of this invention;

FI21G. 2 is a front elevation of the ramjet shown in FIG. 3 is an axial section, partly in elevation, through the forward end of a ramjet illustrating a modification of the embodiment shown in FIG. 1;

FIG. 4 is a front elevation of the ramjet shown in FIG. 3;

FIG. 5 is an axial section, partly in elevation, through the forward end of a ramjet illustrating a second modification of the invention;

FIG. 6 is a front elevation of the ramjet shown in FIG. 5;

FIG. 7 is an axial section, partly in elevation, through the forward end of a ramjet illustrating a third modification of this invention; and

FIG. 8 is a front elevation of the ramjet shown in FIG. 7.

Referring to the drawings, and in particular to FIGS. 1 and 2, there is shown the diffuser section 11 of the body 12 of a ramjet. The diffuser consists, in general, of a cylindrical cowling 13, having a lip 14- and a central duct 15, and an axially located symmetrical center body 16 which tapers to a vertex 17 at its forward end. Suitable struts 18 are provided to hold and aline the center body within the duct 15 in a fixed relationship to the cowling 13, with the vertex 17 of the center body 16located forward of the lip 14. The structure so far described is substantially the Oswatitsch diffuser which is well known in the art.

To overcome the aforesaid objections to the Oswatitsch diffuser, it is necessary, in accordance with the original application of which this application is a continuation-inpart, to secure in front of and in spaced relation to the lip 14 an annular streamlined ring 19. The inner surface 21 of the ring 19 is cylindrically shaped and co axial with the diffuser section. The inside diameter of the ring 19 is greater than the diameter of the circle described by the lip 14. In this manner, the lip 14 projects a short distance into the cylinder described by the inner surface 21 of the ring 19. The leading edge 22 of the ring 19 extends generally in front of the vertex 17 of the center body 16. The aft end 23 of the ring overlaps a portion of the cowling lip 14 and generally extends the contour of the forward end of the cowling 13. A curved surface 25 is provided at the rear end of the ring 19 and is substantially concentric with the contour of the lip 14 of the cowling 13. The angle of the outer surface 24 of the ring 19 may be varied by merely increasing or decreasing the overall length of said ring. The ring 19 is provided with struts 26 which aline and secure said ring to the cowling 13 in a fixed relationship with respect to the center body 16.

By virtue of the position of the ring 19, i.e. being spaced in front of the cowling 13, an annular slot 27 is formed which insures the stability of the diffuser when the latter is subjected to pressure fluctuations during flight. Two splitters 28 and 29, in the form of generally frustoconical bands, are supported by the struts 26 in the slot 27, thus dividing said slot into three smaller but similarly shaped slots. The forwardmost splitter 28 has the same inside diameter as that of the ring 19". However, the aftermost splitter 29 has an inside diameter that is smaller than that of the ring 19 but greater than the inside diameter of the circle described by the lip 14. Hence, the aftermost splitter 29 projects into the cylinder described 3 by the inside diameter of the ring but not as far as does the lip 14.

In operation, the ring 19' prevents the formation of a spurious shock wave at the lip 14 and presents a sharp leading edge 22 to the airstream. Consequently, interference with the beneficial shock waves attached to the lip 14 is eliminated, and the drag forces on the diffuser are reduced.

By the provision of the splitters 28 and 29 within the slot 27, the forward propagation of pressure within said slot is inhibited and the boundary layer along the inner surface 21 is more or less stabilized. However, it has been found that the boundary layer continually builds up and separates from the inner surface 21 regardless of the inhibition of forward pressure propagation. In order to correct for this separation the separated boundary layer is diverted into the outer air stream by the aftmost splitter 29 and the lip 14, thus preventing a disturbance of the beneficial shock wave pattern created by the center body 16.

Any number of splitters may be used to divide the slot 27 into smaller slots and inhibit the forward propagation of pressure to the boundary layer on the inner surface 21 of the ring 1?. For example, as shown in FIGS. 3 and 4, a single splitter 31 of frusto-conical shape may be employed. Similar to the embodiment shown in FIGS. 1 and 2, the ring 19 and splitter 31 have inside diameters that are greater than the circle described by the lip 14. Therefore, the lip 14 diverts the separated boundary layer into the outer air stream to prevent interference with the desired shock wave pattern.

Another modification utilizing two

splitters

32 and 33 and which is not as effective in preventing disturbances to the shock wave pattern but, nevertheless does inhibit the forward propagation of pressure in the slot and thus reduces the frequency of said disturbances, is illustrated in F163. and 6. In this modification the inside diameters of the ring 19, both of the

splitters

32 and 33, and the circle described by the lip 14, are substantially equal. Although interference with the shock wave pattern formed by the center body 16 is not altogether eliminated, it is effectively reduced.

A further modification is shown in FIGS. 7 and 8, and involves the use of two

splitters

34 and 35 to divide the slot 27 into smaller slots. In this instance the inside diameters of the ring and both of the

splitters

34 and 35 are equal but greater than the inside diameter of the circle described by the lip. In addition to the inhibition of forward pressure propagation, the boundary layer is diverted into the outer air stream by the lip 14. In this manner, as explained above, disturbances of the shock wave pattern formed by the center body 16 are averted.

Splitters, similarly applied as those described above, will function equally as well when used in conjunction with the two dimensional wing scoope diffuser provided with a streamlined body as disclosed in the original application. However, splitters of this type will be generally in the form of flat plates that are located in the slot between the lip and the streamlined body.

Obviously many other modifications and variations of the present invention are possible in the light of the above teachings. It is therefore to be understood that within the scope of the appended claims the invention may be practiced otherwise than as specifically described.

What is claimed is:

1. An air inlet for a ramjet, comprising a cowling defining a duct, a body mounted in said duct but partially extending forwardly therefrom, a streamlined member supported in front of and in spaced relation to said cowling and substantially forming an extension of said cowling which is separated therefrom by a slot, said streamlined member being substantially coextensive with the forwardly extending portion of said body and means for dividing said slot into a plurality of slots, whereby said body produces useful shock waves when the ramjet attains supersonic speeds and the separation of the boundary layer from the streamlined member is inhibited by said means. e

2. An air inlet for a rarnjet, comprising a cowling defining a duct, a body mounted in said duct but partially extending forwardly therefrom, a streamlined member supported in front of and in spaced relation to said cowling and generally forming an extension of said cowling which is separated therefrom by a slot, and a circumferentially extending dividing member disposed in said slot to form two slots, whereby said body produces useful shock waves when the ramjet attains supersonic speeds and the separation of the boundary layer from the streamlined member is inhibited by said dividing member.

3. An air inlet for a ramjet, comprising a cowling defining a duct, a body mounted in said duet but partially extending forwardly therefrom, a streamlined member supported in a position in front of and in spaced relation to said cowling, said member substantially corresponding to an extension of said cowling which is separated therefrom by a slot, and a plurality of circumferentially extending dividing members located within the space between said streamlined member and said cowling, whereby said body produces useful shock waves when the ramjet attains supersonic speeds and the separation of the boundary layer from the streamlined member is inhibited by said dividing members.

4. An air inlet for a ramjet, comprising a cowling defining a duct, a body mounted in said duct but partially extending forwardly therefrom, a streamlined member supported in front of and in spaced relation to said cowling and substantially forming an extension of said cowling which is separated therefrom by a slot, and two circumferentially extending dividing members located in said slot to form three smaller slots, whereby said body produces useful shock waves when the ramjet attains supersonic speeds and the separation of the boundary layer from the streamlined member is inhibited by said dividing members.

5. An air inlet for a ramjet, comprising a cowling defining a duct and having a circular lip at its forward end, a center body mounted in said duct and partially extending forwardly therefrom, a streamlined ring having a cylindrical inner surface of greater diameter than that of said circular lip, said ring being positioned coaxially in front of and in spaced relation to said cowling thereby forming a slot between said cowling and said ring, said ring also extending forwardly beyond the forwardly extending portion of the center body, and means for dividing said slot into a plurality of slots.

6. An air inlet for a ramjet, comprising a cowling defining a duct and having a circular lip at its forward end, a center body mounted in said duct and partially extending forwardly therefrom, a streamlined ring having a cylindrical inner surface of substantially the same inside diameter as that of the circular lip, said ring being positioned coaxially in front of and in spaced relation to said cowling thereby forming a slot therebetween, and a pair of spaced dividing members mounted in said slot, said members being generally in the form of bands and having inside diameters substantially equal to those of said streamlined ring and circular lip.

7. An air inlet for a ramjet, comprising a cowling defining a duct and having a circular lip at its forward end, a center body mounted in said duct and partially extending forwardly therefrom, a streamlined ring having a cylindrical inner surface of greater diameter than that of said circular lip, said ring being positioned coaxially in front of and in spaced relation to said cowling thereby forming a slot between said cowling and said ring, and means for dividing said slot into a plurality of slots, said means including a single dividing member generally in the form of a band having an inside diameter equal to that of the streamlined ring.

8. An air inlet for a ramjet, comprising a cowling defining a duct and having a circular lip at its forward end, a center body mounted in said duct and partially extending forwardly therefrom, a streamlined ring having a cylindrical inner surface of greater diameter than that of said circular lip, said ring being positioned coaxially in front of and in spaced relation to said cowling thereby forming a slot between said cowling and said ring, and means for dividing said slot into a plurality of slots, said means including a pair of spaced dividing members generally in the form of bands having inside diameters equal to the inside diameter of the streamlined ring.

9. An air inlet for a ramjet, comprising a cowling defining a duct and having a circular hp at its forward end, a center body mounted in said duct and partially extending forwardly therefrom, a streamlined ring having a cylindrical inner surface of greater diameter than that of said circular lip, said ring being positioned coaxially in front of and in spaced relation to said cowling thereby forming a slot between said cowling and said ring, and means for dividing said slot into a pluraltiy of slots, said means including a pair of spaced dividing members generally in the form of bands, the :forwaIdmost dividing member having an inside diameter substantially equal to that of the streamlined ring and the aftmost dividing member having an inside diameter smaller than that of the streamlined ring but greater than that of the circular lip.

References Cited in the file of this patent UNITED STATES PATENTS 2,631,425 Nordfors Mar. 17, 1953 FOREIGN PATENTS 614,548 Great Britain Dec. 17, 1948