US2563024A

US2563024A - Deflector for resonance combustion chambers

Info

Publication number: US2563024A
Application number: US725804A
Authority: US
Inventors: Esther C Goddard
Original assignee: DANIEL AND FLORENCE GUGGENHEIM
Current assignee: DANIEL AND FLORENCE GUGGENHEIM; DANIEL AND FLORENCE GUGGENHEIM FOUNDATION
Priority date: 1947-02-01
Filing date: 1947-02-01
Publication date: 1951-08-07
Anticipated expiration: 1968-08-07

Description

R. H. GODDARD .DEFLECTOR FOR RESONANCE COMBUSTION CHAMBERS Aug. 7, 1951 Filed Feb. 1, 1947 I N V EN TOR. Reamer f7. Goanmzmfle'c 1). fs THEK C. Gunmen, [ital/mix Patented Aug. 7, 1951 UNITED STATES PATENT OFFICE DEFLECTOR FOR RESONANCE COMBUSTION CHA MBERS Application February 1, 1947, Serial No. 725,804

2 Claims. (01. fill-35.6)

This invention relates to resonance combustion apparatus and more particularly to the combustion chambers of such apparatus.

It is the general object of the present invention to provide a deflector in a resonance combustion chamber which will facilitate in-flow of air and combustion fluids but which will obstruct and retard flow in the reverse or forward direction.

A further object is to provide means for supplying liquid fuel to a resonance combustion chamber and for simultaneously cooling a deflector within such a chamber.

The invention further relates to arrangements and combinations of parts which will be hereinafter described and more particularly pointed out in the appended claims.

Preferred forms of the invention are shown in the drawing, in which Fig. 1 is a sectional side elevation of a resonance combustion chamber embodying the invention;

Fig. 2 is a side elevation of the deflector;

Fig. 3 is a side elevation of a slightly modified deflector; and

Fig. 4 is a sectional view of an aircraft with this invention embodied therein.

Referring to the drawing, portions of a resonance combustion apparatus are shown'comprising an air-collecting portion I 0, a combustion chamber II, and a discharge portion or nozzle l2. All of these parts are preferably enclosed in a jacket casing 14 divided into jacket spaces l5 and I6 by an annular partition H.

The apparatus above described may be mounted in any usual rocket-type aircraft R, as shown in Fig. 4.

A deflector is secured in fixed position in the combustion chamber II by supporting pipes 22. These pipes also connect the jacket space It with the hollow interior of the deflector 20, which preferably has the streamlined contour shown in the drawings. The outer wall portions of the deflector are substantially parallel to the inner wall of the combustion chamber II.

A plurality of concentric tubes 30. 3|, 32 and 33 are mounted within the deflector 20 and extend progressively increasing distances toward the discharge end of the chamber. All of these tubular members are open at their right-hand ends, as viewed in Fig. 1.

Liquid fuel is supplied to the jacket space l5 through a pipe 40 (Fig. 1) and may be sprayed into the annular air-admitting passage 42 through spray openings 43. Any usual ignition and starting means may be provided, as shown for instance in Fig. 22a of Goddard Patent No. 2,395,404, issued February 26, 1946. This patent also shows a storage tank for liquid fuel in 25, and a control valve for the same at I50 in Fig. 26. Additional liquid fuel, either of the same or of different compositions, may be supplied through a feed pipe 45 to the jacket space Hi, from which it is delivered through the pipes 22 to the hollow interior of the deflector 20. The pipes and 45 may be supplied with liquid fuel under pressure fro mstorage tanks T and T.

The inner face of the deflector is preferably provided with annular sets of spray openings 50 through which the liquid fuel may be sprayed into the annular spaces between the tubular members 30 to 33. The deflector and associated sleeves, as well as the combustion chamber wall. are all effectively cooled by the liquid supplied to the jacket spaces l5 and I6.

With the described construction. the streamlined defiector 20 facilitates in-flow of air mixed with fuel through the annular passage 42, but the deflector and associated concentric sleeves retard the flow of air or gases in the opposite direction. The deflector 20 and its associated sleeves are particularly designed to take the place of the movable valve members heretofore used in resonance combustion chambers and to correspondingly simplify the apparatus, but may also be used to supplement such valves by reducing the back pressure thereon.

In Figs. 1 and 2, the concentric sleeves 30 to 33 are cylindrical, while in the modification shown in Fig. 3 a deflector is provided with concentric sleeves 6

l

62 and 63 which are frustroconical. Except for the difference in section of they sleeves, the construction and operation is the same as in Figs. 1 and 2.

Having been thus described, the invention is not to be limited to the details herein disclosed, otherwise than as set forth in the claims, but what is claimed is:

1. In a resonance combustion apparatus, a combustion chamber having air-collecting means adjacent the entrance end thereof, and a streamlined deflector mounted within said chamber and axially disposed relative thereto, the rear face of the deflector being deeply concave and having a pluralityof concentric axiallydisposed sleeves mounted at the concave rear face of said deflector and extending rearward in annular spaced relation, with the annular recesses between said sleeves open at their rear ends, and means to spray liquid fuel into said annular recesses beaseaoae 3 tween said sleeves at the front ends of said recesses.

2. In a resonance combustion apparatus, a combustion chamber of substantially elliptical longitudinal section and having air-collecting means adjacent the entrance thereof, and a streamlined deflector mounted within said chamber and adjacent the entrance thereof and axially disposed relative to said chamber, said deflector comprising a casing shaped to substantially correspond to the inner surface of the entrance end portion of said chamber and substantially uniformly spaced therefrom, said deflector having a plurality of concentric tubes secured to the rear face of said deflector and closed at their front ends thereby, inwardly adjacent tubes being progressively smaller and longer to correspond approximately to the decreasing cross section of the combustion chamber and extending toward the discharge end of said chamber and said tubes being effective to retard return flow of air and combustion gases toward the air-collecting in- 4 take. and. the rear ends 01' said tubes being open and all being substantially equally distant from the inner wall of said combustion chamber at said rear ends.

ESTHER C. GODDARD. Ezecutria: of the Last will and Testament of Robert H. Goddard, Deceased.

' assurances crrsn The following references are of record in the file of this patent:

UNITED STATES PATENTS