RU2730206C1 - Compressed combustion gas-turbine internal combustion engine - Google Patents

Compressed combustion gas-turbine internal combustion engine Download PDF

Info

Publication number
RU2730206C1
RU2730206C1 RU2019125922A RU2019125922A RU2730206C1 RU 2730206 C1 RU2730206 C1 RU 2730206C1 RU 2019125922 A RU2019125922 A RU 2019125922A RU 2019125922 A RU2019125922 A RU 2019125922A RU 2730206 C1 RU2730206 C1 RU 2730206C1
Authority
RU
Russia
Prior art keywords
turbine
blades
gas
engine
centrifugal compressor
Prior art date
Application number
RU2019125922A
Other languages
Russian (ru)
Inventor
Александр Тихонович Зыбин
Original Assignee
Александр Тихонович Зыбин
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Александр Тихонович Зыбин filed Critical Александр Тихонович Зыбин
Priority to RU2019125922A priority Critical patent/RU2730206C1/en
Application granted granted Critical
Publication of RU2730206C1 publication Critical patent/RU2730206C1/en

Links

Images

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/045Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having compressor and turbine passages in a single rotor-module
    • F02C3/05Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having compressor and turbine passages in a single rotor-module the compressor and the turbine being of the radial flow type
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/14Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • F02C3/16Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chambers being formed at least partly in the turbine rotor or in an other rotating part of the plant
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12Cooling of plants
    • F02C7/16Cooling of plants characterised by cooling medium
    • F02C7/18Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22Fuel supply systems
    • F02C7/232Fuel valves; Draining valves or systems

Abstract

FIELD: machine building.SUBSTANCE: invention relates to propulsion engineering, namely to gas turbine engines, and can be used on modern aircraft, sea vessels and tanks. Combustion-ignition internal-combustion gas-turbine engine comprises centrifugal compressor (1), gas centripetal turbine (2) and combustion chamber (3). Centrifugal compressor and gas centripetal turbine are made in one housing rotating about fixed axis. Blades of the centrifugal compressor and turbine are of complex configuration and make an integral part smoothly changing into each other. Width of section of blades of turbine part is twice more than width of section of blades of compressor part. Cavities between vanes and device housing at the point of centrifugal compressor blades transition into turbine ones form combustion chambers with increase of flow section along combustion gases flow direction. Fuel is fed into combustion chambers via channels (4) made in fixed axis and engine housing. Radial fuel channels are equipped with centrifugal valves (5) which open at minimum engine rpm to ensure ignition of fuel, and are closed when maximum permissible rpm is exceeded by strength criteria.EFFECT: technical result consists in improvement of efficiency of gas turbine internal combustion engine with compression from compression due to implementation of centrifugal compressor and gas centripetal turbine in one housing rotating around fixed axis with common blades of complex configuration.1 cl, 1 dwg

Description

The invention relates to the field of engine building, namely to gas turbine engines and can be used on modern aircraft, ships and tanks.

Known "Gas turbine engine", which includes a segment of the annular block of the inlet guide vanes, and when the engine is running, the segment directs hot exhaust gases to the rotor blades of the engine, while the segment includes a platform located on one side of the segment radially inside / outside with respect to axis of rotation of the engine, wherein the platform has a trailing edge portion downstream of the flow of hot exhaust gases through the segment, the trailing edge portion includes a guide that extends radially inward / outward from the trailing edge portion, the engine also includes a support and a cooling device for supporting the segment and directing a cooling fluid for cooling the segment, the device being disposed radially in / outside the platform, the device including a flange portion that extends radially outward / inward of the device, characterized in that the device further includes includes a petal seal and at least one retaining pin, the retaining pin or pins extending through the petal seal, the guide and flange portion to thereby attach the segment to the segment radial positioning device and hold the petal seal in place to seal the contact the surface between the guide and the flange part from the inlet of the cooling fluid.

Patent for invention of the Russian Federation No. 2565127, MKI: F01D 9/04, publ. 08/10/2015. Known "Gas turbine engine, containing, two nodes connected to each other and forming an annular chamber containing a gasket, while two contacting each other annular parts belonging to two nodes, respectively and limiting the said chamber, are pressed together with an axial force, and between their surfaces, an annular intermediate piece is installed end-to-end. Patent for the invention of the Russian Federation No. 2380546, MKI: F02B 75/32, publ. 01/20/2012

The closest analogue to the proposed invention is 1. "Gas turbine engine" containing an asymmetric rotary-type compressor with a small number of blades, a direct-flow combustion chamber and a jet turbine, located on the same axis with the compressor, having a common directional vector of shaft rotation and movement working fluid flow.

2. The engine according to claim 1, characterized in that the blades of the single-section compressor do not have slots, slide along the surface of the housing, and are parallel to the axis of rotation.

3. The engine of claim. 1, characterized in that the compressor casing, which has an oval shape, is asymmetrically located relative to the axis of rotation, which, together with the surface of the rotor, provides volumetric compression of the working fluid.

4. The engine of claim. 1, characterized in that the compressor has the ability to adjust the volume of air supply during engine operation, thereby providing the possibility of a sharp increase or decrease in engine power.

5. The engine of claim. 1, characterized in that the blade built into the turbine rotor slides inside the turbine casing, and the rotor has a gas-water groove and a pre-blade chamber (inter-blade space).

6. The engine according to claim. 1, characterized in that the turbine is in a closed housing having an inlet and an outlet.

RF patent for PM, No. 67186, MKI: F02C 11/00, publ. 02/20/2007.

The technical result is an increase in the efficiency of a gas turbine internal combustion engine with compression ignition due to the implementation of a centrifugal compressor and a gas centripetal turbine in a single housing rotating around a fixed axis with common blades of a complex configuration. In addition, the design of the proposed engine reduces the complexity of its manufacture.

The achievement of this technical result is ensured by the fact that the internal combustion gas turbine engine with compression ignition contains a centrifugal compressor, a gas centripetal turbine and a combustion chamber. The centrifugal compressor and the gas centripetal turbine are made in one casing rotating around a fixed axis. In this case, the blades of the centrifugal compressor and the turbine are made of a complex configuration and make up one whole, smoothly passing into each other. The section width of the turbine section blades is twice the section width of the compressor section blades. In this case, the cavities between the blades and the body of the device at the transition of the blades of the centrifugal compressor to the turbine form combustion chambers with an increase in the flow area along the direction of the combustion gas mixture. Fuel is supplied to the combustion chambers through channels made in the fixed axis and the engine housing. In addition, the radial fuel passages are equipped with centrifugal valves that open at the minimum engine speed, which guarantees fuel ignition, and close when the maximum permissible speed is exceeded according to the strength criteria.

Drawing - Gas turbine engine with compression ignition (general drawing-diagram).

A gas turbine internal combustion engine with compression ignition is illustrated by a drawing. The gas turbine internal combustion engine with compression ignition (drawing) consists of a centrifugal compressor 1 and a gas centripetal turbine 2, located in one casing rotating around a fixed axis. The blades of the compressor 1 smoothly pass into the blades of the turbine 2, they are made of a complex configuration and form with the body of the device at the transition point of the combustion chamber 3, into which the fuel is supplied through the channels 4, it also lubricates the engine bearings. If necessary, a small amount of oil is added to the fuel.

Centrifugal valves 5 are placed in the fuel passages 4. If necessary, ribs can be made on the outer surfaces of the engine to improve cooling. The rotating parts of the engine are made of heat-resistant and heat-resistant materials.

The gas turbine internal combustion engine with compression ignition operates as follows: atmospheric air, entering the compressor part 1, is compressed there and injected into the rotating chamber 3, where it mixes with the fuel supplied through the channels 4 to the same place, and is additionally compressed due to the formation of centrifugal forces from the flow turning and the mixture is flammable. Combustion chambers 3 have flow areas increasing in the direction of movement of burning gases, therefore combustion occurs at constant pressure generated by compressor 1. Fuel channels 4 simultaneously perform the function of a centrifugal fuel pump.

In the radial fuel channels 4 there are centrifugal valves 5, which open at the minimum engine speed, at which the fuel is guaranteed to ignite and close when the maximum allowable speed is exceeded according to strength criteria.

The expansion of the channels - the combustion chambers 3 in the direction of movement of the hot gases is chosen so that combustion takes place at a constant pressure generated by the pump. The blades of the turbine part 2 are made with a section, the width of which is twice the width of the section of the blades of the compressor part 1, in accordance with the expanding flow sections of the combustion chambers 3, therefore, the operation of the turbine 2 is sufficient for the operation of the pump 1 and for obtaining useful mechanical energy. Expansion of gases in turbine 2 occurs to atmospheric pressure. An increase in the efficiency of a gas turbine internal combustion engine with compression ignition is carried out by creating an optimal gas-fuel mixture.

Intensive cooling of a rotating gas turbine internal combustion engine with compression ignition is provided by direct contact of a gas centripetal turbine 2 with ambient air and a relatively cooler centrifugal compressor 1, which makes it possible to bring the compression ratio to the ignition temperature of the fuel and, as a consequence, increase the engine efficiency.

The technical solution proposed as an invention provides an increase in the efficiency of a gas turbine internal combustion engine with compression ignition, in addition, the design of the proposed engine makes it possible to reduce the complexity of its manufacture.

Claims (1)

  1. An internal combustion gas turbine engine with compression ignition, containing a centrifugal compressor, a gas centripetal turbine and a combustion chamber, characterized in that the centrifugal compressor and the gas centripetal turbine are made in one housing rotating around a fixed axis, while the blades of the centrifugal compressor and the turbine are made of a complex configuration and make up one whole, smoothly passing into each other, and the section width of the blades of the turbine section is twice the width of the section of the blades of the compressor section, and the cavities between the blades and the housing of the device at the transition of the centrifugal compressor blades to the turbine form combustion chambers with an increase in the flow section along the course the movement of the combustion gas mixture, fuel is supplied to the combustion chambers through the channels made in the fixed axis and the engine housing, in addition, the radial fuel channels are equipped with centrifugal valves that open at a minimum engine speed i, which guarantees the ignition of the fuel, and close when the maximum permissible speed according to the strength criteria is exceeded.
RU2019125922A 2019-08-15 2019-08-15 Compressed combustion gas-turbine internal combustion engine RU2730206C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2019125922A RU2730206C1 (en) 2019-08-15 2019-08-15 Compressed combustion gas-turbine internal combustion engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2019125922A RU2730206C1 (en) 2019-08-15 2019-08-15 Compressed combustion gas-turbine internal combustion engine

Publications (1)

Publication Number Publication Date
RU2730206C1 true RU2730206C1 (en) 2020-08-19

Family

ID=72086377

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2019125922A RU2730206C1 (en) 2019-08-15 2019-08-15 Compressed combustion gas-turbine internal combustion engine

Country Status (1)

Country Link
RU (1) RU2730206C1 (en)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2709893A (en) * 1949-08-06 1955-06-07 Laval Steam Turbine Co Gas turbine power plant with heat exchanger and cooling means
US3994630A (en) * 1974-08-21 1976-11-30 International Harvester Company Monorotor turbine and method of cooling
EP0206683A2 (en) * 1985-06-17 1986-12-30 University Of Dayton Internal bypass gas turbine engines with blade cooling
US4791784A (en) * 1985-06-17 1988-12-20 University Of Dayton Internal bypass gas turbine engines with blade cooling
RU2702317C1 (en) * 2019-07-01 2019-10-07 Сергей Константинович Исаев Rotary birotate gas turbine engine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2709893A (en) * 1949-08-06 1955-06-07 Laval Steam Turbine Co Gas turbine power plant with heat exchanger and cooling means
US3994630A (en) * 1974-08-21 1976-11-30 International Harvester Company Monorotor turbine and method of cooling
EP0206683A2 (en) * 1985-06-17 1986-12-30 University Of Dayton Internal bypass gas turbine engines with blade cooling
US4791784A (en) * 1985-06-17 1988-12-20 University Of Dayton Internal bypass gas turbine engines with blade cooling
RU2702317C1 (en) * 2019-07-01 2019-10-07 Сергей Константинович Исаев Rotary birotate gas turbine engine

Similar Documents

Publication Publication Date Title
US20170051666A1 (en) Compound cycle engine
US10107195B2 (en) Compound cycle engine
US9194232B2 (en) Compound cycle engine
US9926843B2 (en) Compound cycle engine
US8721291B2 (en) Flow directing member for gas turbine engine
US8087249B2 (en) Turbine cooling air from a centrifugal compressor
US4683716A (en) Blade tip clearance control
US5524587A (en) Sliding vane engine
EP2927428A1 (en) Enclosed baffle for a turbine engine component
EP2450532B1 (en) Rotor blades
US3936215A (en) Turbine vane cooling
KR100737377B1 (en) Variable geometry turbocharger with sliding piston
US8091365B2 (en) Canted outlet for transition in a gas turbine engine
US4314791A (en) Variable stator cascades for axial-flow turbines of gas turbine engines
US4169692A (en) Variable area turbine nozzle and means for sealing same
RU2531110C2 (en) Gas-turbine unit and unit with injector vanes (versions)
RU2530685C2 (en) Impact action structures for cooling systems
EP2578803B1 (en) Methods and systems for use in regulating a temperature of components
CN101688448B (en) Turbine arrangement and method of cooling a shroud located at the tip of a turbine blade
US7334983B2 (en) Integrated bladed fluid seal
US5509388A (en) Internal combustion rotary engine
US3314651A (en) Sealing device
US8167547B2 (en) Gas turbine engine with canted pocket and canted knife edge seal
US8231353B2 (en) Methods and apparatus relating to improved turbine blade platform contours
US9896998B2 (en) Compound engine assembly with modulated flow