CN-115306553-B - Turbojet engine

CN115306553BCN 115306553 BCN115306553 BCN 115306553BCN-115306553-B

Abstract

A turbojet engine comprises a main body, a compressor impeller, a turbine, a rotating shaft, an air supply device and an oil supply device, wherein a first combustion chamber and a second combustion chamber are arranged in the main body, the second combustion chamber is provided with a functional structure, the compressor impeller is arranged in the main body and forms an air inlet path with the main body, the turbine is arranged in the main body and forms an air injection path with the main body, the second combustion chamber is arranged outside the turbine in a surrounding mode, the rotating shaft is rotatably arranged in the main body, the compressor impeller and the turbine are arranged on the rotating shaft, the first combustion chamber is arranged between the compressor impeller and the turbine and is arranged outside the rotating shaft in a surrounding mode, and the oil supply device is arranged on the main body and is used for supplying fuel to the first combustion chamber and the second combustion chamber. In the operation state of the turbojet engine, the compressor impeller rotates to enable external air to be sent to the first combustion chamber and the second combustion chamber through the air inlet path in a pressure mode, fuel in the first combustion chamber is ejected to the outside through the air injection path after being combusted, fuel in the second combustion chamber is ejected to the outside through high-temperature and high-pressure tail gas after being combusted in a knocking mode, and unit head-on thrust of the turbojet engine is larger.

Inventors

HE JIAXIANG
DONG KUN
YIN FAHUI
ZHAO XUESONG
ZHOU KUOHAI

Assignees

清航空天(北京)科技有限公司
清航空天(北京)科技有限公司

Dates

Publication Date: 20260421
Application Date: 20220805
Priority Date: 20220805

Claims (9)

1. A turbojet engine, comprising: The fuel combustion device comprises a main body, wherein a first combustion chamber and a second combustion chamber are arranged in the main body, the second combustion chamber is provided with a functional structure, and the functional structure is arranged to enable the mode of fuel oil in the second combustion chamber during combustion to be a knocking mode; a compressor impeller provided in the main body and configured to construct an intake path with the main body; A turbine, which is arranged in the main body and constructs a jet path with the main body, and the second combustion chamber is arranged outside the turbine in a surrounding way; The rotating shaft is rotatably arranged in the main body, the compressor impeller and the turbine are arranged on the rotating shaft, and the first combustion chamber is positioned between the compressor impeller and the turbine and is surrounded outside the rotating shaft; The oil supply device is arranged on the main body and is used for supplying fuel oil to the first combustion chamber and the second combustion chamber; The air inlet of the first combustion chamber and the air inlet of the second combustion chamber are communicated with the air outlet of the air inlet path, the air outlet of the first combustion chamber is communicated with the air inlet of the air injection path, and the air outlet of the second combustion chamber, the air outlet of the air injection path and the air inlet of the air inlet path are all communicated with the outside; The main body includes: the annular casing is provided with the compressor impeller and the turbine inside; The device comprises a shaft sleeve, a diffuser, a guide and an inner spray pipe, wherein the shaft sleeve, the diffuser, the guide and the inner spray pipe are arranged in the casing, the diffuser and the guide are both fixed on the shaft sleeve, the inner spray pipe is fixed on the guide, and the rotating shaft is rotatably arranged in the shaft sleeve; An injection ring arranged between the inner spray pipe and the casing and fixed on the guide, wherein the injection ring and the casing construct the second combustion chamber; The first combustion chamber component is provided with the first combustion chamber, the shaft sleeve, the casing, the diffuser, the guide and the injection ring form a containing cavity, the first combustion chamber component is arranged in the containing cavity, and the air outlet of the air inlet path, the air inlet of the first combustion chamber and the air inlet of the second combustion chamber are communicated with the containing cavity; The fuel injection device comprises a fuel injection ring, a guide device, a fuel supply device and a fuel tank, wherein the fuel injection ring is fixed by the guide device through a flange structure, the functional structure comprises a plurality of fuel injection holes which are sequentially arranged along the circumferential direction of a second combustion chamber, the fuel supply device comprises a fuel supply pipe which is communicated with the fuel injection holes and is used for supplying fuel from the fuel injection holes to the second combustion chamber, and the other end of the fuel supply pipe is communicated with the fuel tank outside the cartridge receiver after sequentially passing through the accommodating cavity, the diffuser and the cartridge receiver.
2. The turbojet engine of claim 1 wherein the second combustion chamber is of annular configuration and the functional configuration is arranged such that the mode of fuel within the second combustion chamber when combusted is a rotational detonation mode.
3. The turbojet engine of claim 2 wherein the plurality of fuel injection holes each face the air outlet side of the second combustion chamber, and the injection directions of the plurality of fuel injection holes each deflect toward the same side in the circumferential direction of the rotary shaft as the axis of the rotary shaft.
4. The turbojet engine of claim 3 wherein the inner side of the second combustion chamber is provided with a raised structure having a first inclined surface facing the air inlet side of the second combustion chamber and a second inclined surface facing the air outlet side of the second combustion chamber, the plurality of fuel injection holes being located on the second inclined surface.
5. The turbojet engine of claim 3 wherein the number of the plurality of fuel injection holes is not less than 72.
6. The turbojet engine of claim 3 wherein the nozzle aperture of each of the oil jets is 0.2 mm to 0.5mm.
7. The turbojet engine of claim 1 wherein the air outlet of the second combustion chamber and the air outlet of the jet passage are in the same jet direction.
8. The turbojet engine of any one of claims 1 to 7 wherein the turbine is located between the pilot and the inner nozzle, the compressor wheel, diffuser and casing forming the inlet air path, the pilot, turbine and inner nozzle forming the air injection path, the air inlet of the air injection path being located on the pilot and the air outlet of the air injection path being located on the inner nozzle.
9. The turbojet engine of claim 1 wherein the compressor wheel is a centrifugal wheel and the clearance between the centrifugal wheel and the casing is 0.2 mm to 0.5mm.

Description

Turbojet engine Technical Field The present disclosure relates to engine equipment, and more particularly to a turbojet engine. Background The unit head-on thrust is an important index of the turbojet engine, and for the microminiature turbojet engine, the unit head-on thrust of the turbojet engine is low due to the fact that the unit head-on thrust is limited by cost and structural size and cannot be designed by adopting high circulation parameters, the design pressure ratio and the temperature before the turbine are low, and the compressor impeller adopts a centrifugal structure. How to increase the unit head-on thrust of the turbojet engine is always a technical problem which is solved by the person skilled in the art. Disclosure of Invention In order to solve at least one of the above technical problems, the present application provides a turbojet engine with a larger unit head-on thrust in an operating state. The turbojet engine comprises a main body, a compressor impeller, a turbine, a rotating shaft, an oil supply device and an oil supply device, wherein a first combustion chamber and a second combustion chamber are arranged in the main body, the second combustion chamber is provided with a functional structure, the functional structure is used for enabling fuel in the second combustion chamber to be in a knocking mode when in combustion, the compressor impeller is arranged in the main body and forms an air inlet path with the main body, the turbine is arranged in the main body and forms an air injection path with the main body, the second combustion chamber is arranged outside the turbine in a surrounding mode, the rotating shaft is rotatably arranged in the main body, the compressor impeller and the turbine are arranged on the rotating shaft, the first combustion chamber is arranged between the compressor impeller and the turbine and is arranged outside the rotating shaft in a surrounding mode, the oil supply device is arranged on the main body and is used for supplying fuel to the first combustion chamber and the second combustion chamber, an air inlet of the first combustion chamber and the air inlet of the second combustion chamber are communicated with an air outlet of the air inlet path, an air outlet of the first combustion chamber is communicated with an air outlet of the air inlet path, an air outlet of the air inlet of the air injection path of the second combustion chamber is communicated with the air inlet of the air inlet path, and an air outlet of the air inlet path of the air injection path of the second combustion chamber is communicated with the outside. The main body includes: the annular casing is provided with the compressor impeller and the turbine inside; The device comprises a shaft sleeve, a diffuser, a guide and an inner spray pipe, wherein the shaft sleeve, the diffuser, the guide and the inner spray pipe are arranged in the casing, the diffuser and the guide are both fixed on the shaft sleeve, the inner spray pipe is fixed on the guide, and the rotating shaft is rotatably arranged in the shaft sleeve; An injection ring arranged between the inner spray pipe and the casing and fixed on the guide, wherein the injection ring and the casing construct the second combustion chamber; The first combustion chamber component is provided with the first combustion chamber, the shaft sleeve, the casing, the diffuser, the guide and the injection ring form a containing cavity, the first combustion chamber component is arranged in the containing cavity, and the air outlet of the air inlet path, the air inlet of the first combustion chamber and the air inlet of the second combustion chamber are communicated with the containing cavity; The fuel injection device comprises a fuel injection ring, a guide device, a fuel supply device and a fuel tank, wherein the fuel injection ring is fixed by the guide device through a flange structure, the functional structure comprises a plurality of fuel injection holes which are sequentially arranged along the circumferential direction of a second combustion chamber, the fuel supply device comprises a fuel supply pipe which is communicated with the fuel injection holes and is used for supplying fuel from the fuel injection holes to the second combustion chamber, and the other end of the fuel supply pipe is communicated with the fuel tank outside the cartridge receiver after sequentially passing through the accommodating cavity, the diffuser and the cartridge receiver. In some exemplary embodiments, the second combustion chamber is an annular structure and the functional structure is configured such that a mode of fuel within the second combustion chamber when combusted is a rotational detonation mode. In some exemplary embodiments, the plurality of oil jet holes are each directed to the air outlet side of the second combustion chamber, and the injection directions of the plurality of oil jet holes are each deflected toward the same side in the circumferenti