GB837738A - Improvements in or relating to rotary injection devices for gas turbine combustion chambers - Google Patents
Improvements in or relating to rotary injection devices for gas turbine combustion chambersInfo
- Publication number
- GB837738A GB837738A GB39552/57A GB3955257A GB837738A GB 837738 A GB837738 A GB 837738A GB 39552/57 A GB39552/57 A GB 39552/57A GB 3955257 A GB3955257 A GB 3955257A GB 837738 A GB837738 A GB 837738A
- Authority
- GB
- United Kingdom
- Prior art keywords
- cavity
- fuel
- tube
- gas turbine
- axis
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
837,738. Gas turbine plant. SZYDLOWSKI, J. Dec. 19, 1957 [Jan. 8, 1957], No. 39552/57. Class 110 (3). [Also in Group XI] A centrifugal liquid fuel atomizer device for a gas turbine annular combustion chamber 1 having a radial combustion zone 2 comprises a rotatable distributing wheel 15 formed on its periphery with spaced injection holes 20 opening into a cavity 22 formed in said wheel and a tube 23 coaxial with the axis of rotation for supplying the cavity 22 with fuel and provided with means for forming at its outlet a uniform fuel film coaxial with said axis, said cavity 22 being connected with the injection holes 20 through one or more channels formed at the periphery of the cavity 22. As shown, a plurality of radial ducts 17 connect the cavity 22 with respective injection holes 20 and these latter are inclined alternately to one side and the other of a plane perpendicular to the axis of rotation. In another embodiment described in Figs. 1-3 (not shown), the radial ducts are replaced by an annular peripheral channel of rectangular cross-section running round the cavity 22 and the injection holes open into the channel at points spaced from the bottom of the channel. The tube 23 is formed over its inner surface with splines 25, Fig. 5, which merge at their ends into an enlarged smooth surface 26 adjacent the tube outlet so as to form the fuel into a uniform film coaxial with the axis of rotation and cross webs may be provided in the tube inlet downstream of a fuel feeding nozzle so as to impart rotary motion to the fuel fed through the nozzle. The cavity 22, formed of a blind bore 18 ground or polished, is closed by a steel sleeve 21 fitted into the bore and welded to the wheel 15, which in turn is welded at 16 to the central shaft 3 of the gas turbine. The fuel supply tube 23 extends coaxially through the sleeve 21 being guided in the bore 18 by a radial flange 24, the engaging surfaces being ground to fit as also the inner peripheral surface of the wheel and the engaging outer surface of the flange, for the removal of the tube and, to ensure perfect sealing, rubber rings 27 associated with discs 28 are maintained within the sleeve 21 by circlips 29. Specification 686,908 is referred to.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR1096686X | 1957-01-08 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB837738A true GB837738A (en) | 1960-06-15 |
Family
ID=9618286
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB39552/57A Expired GB837738A (en) | 1957-01-08 | 1957-12-19 | Improvements in or relating to rotary injection devices for gas turbine combustion chambers |
Country Status (3)
| Country | Link |
|---|---|
| DE (1) | DE1096686B (en) |
| FR (1) | FR1164675A (en) |
| GB (1) | GB837738A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2197911A (en) * | 1986-07-28 | 1988-06-02 | Teledyne Ind | Fuel supply path in a gas turbine engine |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115899769A (en) * | 2022-10-17 | 2023-04-04 | 南京航空航天大学 | Combustion chamber with coupled inner-stage concave cavity and outer-stage rotational flow |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR785802A (en) * | 1935-02-18 | 1935-08-20 | Oil burner and other fuel oil | |
| DE847530C (en) * | 1944-11-17 | 1952-08-25 | Hellmut Weinrich | Annular combustion chamber, especially for gas turbines |
| FR1011066A (en) * | 1948-11-30 | 1952-06-18 | Combustion chamber |
-
1957
- 1957-01-08 FR FR1164675D patent/FR1164675A/en not_active Expired
- 1957-03-04 DE DES52584A patent/DE1096686B/en active Pending
- 1957-12-19 GB GB39552/57A patent/GB837738A/en not_active Expired
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2197911A (en) * | 1986-07-28 | 1988-06-02 | Teledyne Ind | Fuel supply path in a gas turbine engine |
| GB2197911B (en) * | 1986-07-28 | 1991-03-20 | Teledyne Ind | Turbine shaft fuel pump |
Also Published As
| Publication number | Publication date |
|---|---|
| DE1096686B (en) | 1961-01-05 |
| FR1164675A (en) | 1958-10-13 |
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