US2428330A

US2428330A - Assembly of multistage internalcombustion turbines embodying contrarotating bladed members

Info

Publication number: US2428330A
Application number: US517273A
Authority: US
Inventors: Heppner Fritz Albert Max
Original assignee: Armstrong Siddeley Motors Ltd
Current assignee: Armstrong Siddeley Motors Ltd
Priority date: 1943-01-15
Filing date: 1944-01-06
Publication date: 1947-09-30
Anticipated expiration: 1964-09-30

Description

Sept 30, 1

947- F. A. M. HEPPNER 2,428,330 ASSEIBLY OF IULTISTAGE INTERNAL-COIBUSTION TURBINES EIBODYING CONTRA-ROTATING BLADED HEIBBRS Filed Jan. s. 1944 a Sheets-Sheet 1 EWING) pt- 30, 1947- F. A. M. HEPPNER 2,428,330

ASSEIBLY 0F IULTISTAGB INTERNALrCOIBUSTION TURBINBS BIBQDYIHG' CONTRA-BUTATING BLADED IEIBERS I Filed Jan. 6, 1944 5 Sheets-Sheet 2* INVENTOK Zn 5 M M PF 1947. F. A. M; HEPPNER 2 42 LSSEIBLY 0F IULTISIAGE IIITBRm-COIBUSTIOK TURBIIBS HBODYIIG COHTRA-EOTATIHG BLAD mm Filed Jan. 6, 1944 3 Shasta-Sheet 3 Patented Sept. 30, 1947 ASSEMBLY COMBUSTION F MULTISTAGE INTERNAL-.

TURBINES EMBODYING CONTRABOTATING BLADED MEMBERS Fritz Albert Max Heppner, Leamington Spa, England, assignor to Armstrong Sidd ley Motors Limited, Coventry, England Application January 6, 1944, Serial No. 517,273 In Great Britain January 15, 1943 1 This invention relates to a multi-stage-interpal-combustion turbine plant, and particularly to a compound, internal-combustion, turbine plant for jet-propulsion purposes, the plant having a contra-rotating shell carrying externally jet-augmenter blades.

My main object is to facilitate assembly of the parts.

For an understanding of this and of other objects and advantages of the invention attention Claims. (Cl. (ill-35.6)

form of sprays l1 from suitable orifices in a hollow feed nozzle sleeve 34, and is provided with a plurality of elbow-shaped tubular members l8 which extend axially toward and deliver the prodnets of combustion to the inlet of the turbine. Each of the tubular members I8 is also provided with a plurality of holes 38 communicating with an annular space 411 to which the remainder of should be directed to the following description, in

which one arrangement, according to the invention, is described with reference to the accompanying diagrammatic drawings, in which- Figure 1 is a part-sectional elevation of a Jetpropulsion turbine plant; and

Figures 2, 3 and 4 are views mainly of one of the independent turbine and compressor sections, Figure 2 being a perspective view of the shell with the augmenter blades omitted and with one in-. dependent turbine and compressor section shown withdrawn, whilst Figure 3 is an axial view thereof and Figure 4 a fragmentary developed plan of the independent section.

According to the invention, there are outwardly-extending compressor and/or turbine blade rows on an inner member or members coacting with inwardly-extending blade rows on an outer member or members, and the blades in each row are arranged and spaced from one another so as to admit of axial assembly of the said inner and outer members after the blades have been secured in position. Consequently, the outer member (or the output of the compressor is delivered in the manner indicated at the lower left-hand portion of Figure 1. 1

The burning gases, mixed with the diluent air entering through the holes, 39, are led from the tubular members [8 to a stationary row of blades l9 forming nozzles through which the gases pass at high speed to the first row 20 of turbine blades mounted on the shell 2|, these blades being partly or wholly of the impulse type. (The shell carries external augmenter blades 22 coacting with stationaryaugmenter blades 23.) The next row of turbine blades l5a fast on the sleeve it rotates at high speed to drive the final portion of H the compressor, this row and the next row 24 (on the shell) being of the reaction type. The final independent rows 15 and the coacting blades 25 x are all of the aerofoil type.

members) need not be split, 1. e., it (or they) may be integrally formed.

Referring now to Figures 1 to 4, the plant illustrated is one in which the turbine II is disposed radially outwardly of the compressor l2, the flow through the latter being from the top to the bottom, i. e., from the jet end to the front. The compressor comprises stationary blade rows l3, l3 and rotary rows l4, l4, the latter rows being fast with independent turbine rows l5, l5 from which they are shielded by shrouds. The first independent turbine row l5a is mounted to revolve with a sleeve I6 carrying a plurality of compressor rows Ila coacting with stationary compressor rows i3a.

The primary output of the compressor flows, as indicated by the arrows, around and into the combustion chamber 38, which may be or any suitable construction. As shown, the chamber 38 is annular in form, open at its radially inner surface to receive the primary air required for combustion and the injected fuel which issues in the As will be seen from Figures 2, 3 and 4 the blades l5 are spaced from one another sufiiciently to allow of assembly into the shell through the larger (top in Figure 1) end thereof, the blades passing between the blades 25 fast with the shell.

As each disc It has only a single compressor row the power to drive it is small enough to allow wide spacing of the turbine blades without excessive lift figures on the turbine blades. In other words, the turbine blades in a row have only small deflections.

Figure 4 shows at Mb some of the compressor blades strengthened to carry the centrifugal forces.

Conveniently theshel1 2| is mainly of aluminium, the blades 25 being carried by ring sections 21 having end clearance from one another when cold, as indicated at 28 (Figure 3), the portions 21 being riveted at 29 to aluminum ribs 30 with heat insulating material 3| interposed. Alternatively, the shell can be made from steel in one piece with the turbine blades 25 permanently fixed in it, this being possible by the new way of assembly as a consequence of the wide spacing of the turbine blades. assembling and dismantling the shell without interl'ering with the balance, which is a very important point because of the relatively great weight of the shell.

This feature. also allows of- I, in a similar way the blade rows Ila are arranged so that they can be slid axially between the stationary blade rows l3a.

At 33 I shows; drive shaft, for auxiliaries, pass- L ing through the hollow feed nozzle 34, the drive shaft carrying a, gear 35 which is driven from the compressor sleeve l6 through a compound pinion 36 and gear 31.

. What I claim as my invention and desire to, secure by Letters Patent of the United States is" 1. In an internal-combustion turbine plant, a

rotating shell carrying inwardly-extending blade rows, coacting contra-rotating blade rows, and a plurality of compressor portions rotatably mounted within said shell, each of said contra-rotating blade rows being carried by and driving one of said compressor portions, the blades in said rows being spaced circumferentially and arranged so that said compressor portions can be inserted into said shell in an axial direction after said blades have been secured in position. V

2. In an internal-combustion turbine plant, a. rotating shell carrying inwardly-extending turbine blade rows, contra-rotating shrouds within coacting turbine blade row and also an inwardly-extending compressor blade row, and coasting stationary compressor blade rows, the blades in said rows being spaced clrcumferentially and arranged so that said shrouds can be inserted into said shell in an axial direction after said blades have been secured in position. 3. Apparatus as defined in claim 2, includin outwardly-extending jet-augmenter blade rows 4 tion with its blades passing between said stationary blades to bring said blade rows into 00- acting position.

4. In an internal-combustion turbine plant, a

rotating shell carrying inwardly-extendingturbine blade rows, a'support extending axially through said shell, contra-rotating shrouds within said shell each carrying an outwardly-extending coacting turbine blade row and also an inwardly-extending compressor ,blade row, said shroud rings being rotatably mounted on said support, and enacting stationary compressor blade rows mounted on said support between said rotatable compressor blade rows, the blades or said turbine blade rows being spaced circumferentially and arranged so that said shrouds can be inserted into said shell in an axial direction after said blades have been secured in position.

5. In an internal-combustion turbine plant, an outer shell having inwardly-extending blade rows. and a member within said shell having coacting outwardly-extending blade rows, said shell and member being mounted for relative rotation, the

. blades of said rows being spaced circumferentialsaid shell each carrying an outwardly-extending on said shell and coacting stationary jet-augmenter blade rows, the augmenter blades of said rows being spaced circumferentially and arranged ly and arranged so that said member may be moved axially into coacting position -within said shell with the blades secured in position on said shell and member.

FRITZ ALBERT MAX HEPPNER.

REFERENCES CITED The following references are of record in the- Number Name Date 710,884 Parsons Oct. 7, 1902 980,644 Knight Jan. 3, 1911 1,016,080 McCulloch Jan. 30, 1912 Roder May 20, 1930