Combustion chamber for gas turbine专利检索-发散冷却空气动力学专利检索查询-专利查询网

Combustion chamber for gas turbine

阅读：126发布：2021-10-06

专利汇可以提供Combustion chamber for gas turbine专利检索，专利查询，专利分析的服务。并且Combustion chamber for a gas turbine, comprising two concentric sheet metal casings where the air enters and the compressed gases circulate in contra-current, chiefly notable in that the exterior casing, open at one end to receive the air, is closed at the other end by a cap provided with radial ribs which surround a central jet provided to inject an atomized combustible liquid, this jet opening onto one extremity of the interior casing where it is surrounded by profiled blades fixed slantwise to rotate the air, while this inner casing defines an expanded zone provided with a large number of small slots for the admission of the primary air of combustion, this expanded zone being extended by a short convergent part into which open lateral slots of relatively large diameter for the admission of second air after which the inner casing is continued up to the escape extremity by a divergent zone having wide lateral slots for the admission of coolant air, these slots being surrounded by a deflector fixed on the exterior of the inner shell with a view to prevent the formation of directly opposed currents of air admitted into the combustion chamber. This combustion chamber can, moreover, show the following characteristics envisaged separately or in combination: 1. An odd number of secondary air slots and an also odd number of slots for the mixing of coolant air. 2. Lateral slots for the secondary air are each provided with a tubular portion which is inclined towards the jet in the direction of the general axis of the chamber. 3. Two combustion chambers of this type are used, mounted parallel to one another in the same transverse plane with reference to the general axis of the turbine, their equilibration being assured by means of a by-pass channel which connects the two expanded zones of the two internal casings.，下面是Combustion chamber for gas turbine专利的具体信息内容。

权利要求

1. A combustion chamber for a gas turbine comprising inner and outer concentric casings wherein the inlet air travels in one direction within the inner casing, said outer casing being closed at one end with a plurality of radially extending ribs secured internally thereof and surrounding the corresponding end of said inner casing, fuel injection means secured in the closed end of said outer casing and disposed concentrically with respect to said inner and outer casings, said inner casing defining an annular opening about said fuel injection means, blade means disposed in said annular opening to form a vortex from the passing air, an expansiOn chamber formed by said inner casing downstream from said blade means and having a diameter larger than the diameter of said annular opening, a plurality of primary and secondary air openings formed through said expansion chamber, said inner casing diverging outwardly downstream from said expansion chamber, cooling slots extending through the diverging portion of said inner casing, and annular deflector means secured to said diverging portion downstream of said slots and substantially overlying said slots in spaced relation intermediate said casings to prevent the direct flow of inlet air into said cooling slots.

2. A combustion chamber as set forth in claim 1 wherein said secondary air openings are larger than and disposed downstream from said primary air openings in said expansion chamber, said secondary air inlet openings being odd in number and disposed circumferentially about said combustion chamber.

3. A combustion chamber as set forth in claim 1 further comprising additional air opening means formed in said diverging portion immediately downstream of said secondary air inlet openings which are smaller than said secondary air inlet openings.

4. A combustion chamber as set forth in claim 3 wherein said cooling air slots are disposed downstream of said additional air openings, said cooling slots being odd in number and disposed circumferentially about said diverging portion.

5. A combustion chamber as set forth in claim 1 wherein said annular deflector means has a truncated conical configuration with the smaller diameter portion being secured to said diverging portion of said inner casing downstream of said cooling slots.

6. A combustion chamber as set forth in claim 1 further comprising retractable spark plug means movable between a working position wherein said plug means extends into the inner casing and a retracted position wherein said plug means does not extend into said inner casing, spring means normally biasing said plug means into said working position and piston means responsive to increased pressures for retracting said plug means during self-sustained operation of the gas turbine.

7. A combustion chamber as set forth in claim 1 wherein said fuel injection means is comprised of a spray nozzle extending into said inner casing, feed channel means, return channel means, valve means for controlling the communication of said feed channel means with said spray nozzle said return channel means, and electromagnetic means for shifting said valve means to control the flow of fuel through said spray nozzle into said combustion chamber.

8. In a gas turbine engine of the type having a compressor means, turbine means, and a pair of combustion chambers intermediate said compressor means and said turbine means, the improvement comprising inner and outer concentric casings wherein the inlet air travels in one direction between said casings and said outlet gases travel in the opposite direction within the inner casing, said outer casing being closed at one end with a plurality of radially extending ribs secured internally thereof and surrounding the corresponding end of said inner casing, fuel injection means secured in the closed end of said outer casing and disposed concentrically with respect to said inner and outer casings, said inner casing defining an annular opening about said fuel injection means, blade means disposed in said annular opening to form a vortex from the passing air, an expansion chamber formed by said inner casing downstream from said blade means and having a diameter larger than the diameter of said annular opening, a plurality of primary and secondary air openings formed through said expansion chamber, said inner casing diverging outwardly downstream from said expansion chamber, cooling slots extending through the diverging portion of said inner casing, and annular deflector means secured to said diverging portion downstream of said slots and substantially overlying said slots in spaced relation intermediate said casings to prevent the dIrect flow of inlet air into said cooling slots.

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Combustion chamber for gas turbine

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