Novel turbine engine

Abstract

The invention relates to the field of turbine engines, and discloses a design of a novel efficient energy-saving turbine engine. The efficiency of a turbine engine generally ranges from 30% to 40%, a large amount of energy cannot be utilized and is wasted along with operation of the engine, and the turbine engine aims at utilizing the wasted energy, improving the efficiency of the turbine engine and improving the output power of the engine while fuel consumption is not increased. And the technical progress in the field of turbine engines in China is promoted.

Description

Technical Field

[0001] This patent relates to the field of turbine engines, and the design is a new type of high-efficiency and energy-saving turbine engine. Background Technology

[0002] The main working principle of a turbine engine is as follows: Air first enters the compressor, is compressed, and then sent to the combustion chamber. In the combustion chamber, the air mixes with fuel and burns, releasing high-temperature, high-pressure combustion gases. These gases flow through the turbine blades, where they perform work, driving the compressor and other accessories, and ultimately outputting power. Currently, the efficiency of turbine engines is generally between 30% and 40%, meaning a significant amount of energy is wasted during engine operation.

[0003] Turbine engines are primarily used in power generation and aviation. Their application in marine engineering, petrochemicals, and shipbuilding is also gradually increasing. Furthermore, their use in emerging markets such as new energy power generation and industrial parks is also growing.

[0004] We will use aircraft engines as an example to explain the current state of turbine engines. The research and production of turbine engines is an extremely complex systems engineering project, characterized by high technological barriers, high R&D investment, long development cycles, and high capital expenditure requirements. It needs to operate under extremely harsh conditions of high temperature, high pressure, and high stress, while ensuring long-term, high-level stable operation. As aircraft become larger, the demand for engine thrust continues to grow, leading to continuous improvements in the safety, reliability, and durability of turbine engines. High-thrust engines enable aircraft to carry more equipment and fuel, transport more passengers, and fly faster, higher, and farther. To address this issue, in recent years, engine engineers both domestically and internationally have generally focused on increasing the engine's specific thrust (thrust / air mass flow rate), increasing the turbine inlet gas temperature, and increasing the engine's bypass ratio, among other important design parameters. However, these areas have been under development for many years, and significant breakthroughs are difficult to achieve. Summary of the Invention

[0005] This invention patent designs a novel turbine engine that can increase engine efficiency, reduce the gas temperature before the turbine, and increase the service life of the engine core.

[0006] To achieve the above objectives, this invention requires some improvements to the original turbine engine. The improvements include: creating a ring of small holes (e.g., on the turbine casing around the outer ring of the high-pressure turbine guide vanes) on the turbine housing. Figure 1 At point A shown, an opening is made to connect a water pipe. The water pipe contains water with a certain pressure, and there is a valve on the water pipe to control the flow rate and the opening and closing of the water flow.

[0007] When the engine is running normally after starting, or during startup, the valve on the water pipe is opened to allow water in the pipe to be sprayed into the high-pressure turbine guide vanes at a certain flow rate. At this time, the high-temperature combustion gas in the high-pressure turbine guide vanes will mix with the water. The water sprayed into the high-pressure turbine guide vanes will turn into a gaseous state after absorbing heat, forming high-pressure water vapor. At this time, the gas sprayed onto the high-pressure turbine blades becomes a mixture of water vapor and combustion gas. The pressure of the mixed gas is significantly higher than the pressure of the pure high-temperature combustion gas before mixing. This pressure is the source of the turbine's operation.

[0008] After water is injected into the guide vanes of the high-pressure stage turbine, the gas temperature before the high-pressure turbine drops significantly, greatly improving the turbine's operating environment. The turbine is no longer subjected to high-temperature thermal stress, centrifugal force, and aerodynamic forces, but rather to medium- and low-temperature thermal stress, aerodynamic forces, and centrifugal force. Of these three forces, high-temperature thermal stress causes the most damage to the turbine blades, and only thermal stress cannot perform external work. The water injection significantly lowers the operating temperature of the turbine blades and guide vanes, drastically reducing the thermal stress they bear, especially on the high-pressure stage turbine blades. This reduction in thermal stress allows the turbine blades to withstand greater centrifugal and aerodynamic forces, which are crucial for turbine operation. This results in greater power output from the turbine, thus increasing the overall engine power output.

[0009] After water is injected into the engine, the temperature of the gas in front of the turbine will decrease. The decrease in the gas temperature in front of the turbine improves the working environment of the entire turbine system, making the turbine's working environment move towards a lower temperature, reducing the damage of high temperature to the turbine, thus extending the working life of the turbine, thereby increasing the working life of the entire engine.

[0010] The control of the engine water injection volume is achieved by constantly monitoring the engine exhaust temperature (EGT) through a computer during actual engine operation. This ensures that the engine exhaust temperature (EGT) does not fall below 100°C. When the engine exhaust temperature (EGT) falls below 100°C, it indicates that the mixture of water vapor and high-temperature combustion gas releases excessive energy during operation in the turbine. This situation causes some water to change from a gaseous state to a liquid state in the turbine. The liquid state of the water in the turbine will cause the pressure of the mixture to drop, thereby affecting the operation of the turbine.

[0011] The reason for the increased engine efficiency is that this engine utilizes energy that cannot be utilized by conventional engines. Taking an aircraft turbine engine as an example, the exhaust temperature (EGT) of an aircraft turbine engine is normally 800°C during cruise. If the engine designed according to this invention is used, its exhaust temperature will be maintained at 100°C. This engine utilizes the energy contained in the temperature difference between these two exhaust temperatures, converting the energy contained in the temperature difference into engine output power, thereby improving the engine's working efficiency.

[0012] The water jet in the engine is sprayed in the direction of the high-temperature gas flow within the high-pressure turbine guide vanes, and sprayed from the casing at the turbine guide vanes into the inner side of the turbine guide vanes. There are water nozzles in the channel formed by every two high-pressure turbine guide vanes, and the water output is the same. The purpose of this design is to ensure that a uniform and stable cooling zone is formed within the entire circle of high-pressure turbine guide vanes of the engine.

[0013] The engine's water supply system consists of a water tank, a booster pump, various pipelines, flow control valves, and various insulation and heating elements. Taking an aircraft engine as an example, since the temperature in the air is generally below -30 degrees Celsius after the aircraft takes off, water easily freezes at this temperature. The water in the tank and the pipelines need to be heated and insulated to ensure that the water does not freeze. Each section of the water pipeline is wrapped with insulation cotton and has internal heating elements. The water tank is wrapped with insulation cotton and has heating elements inside to ensure that the water does not freeze during flight. A lubricating oil-water heat exchanger can also be installed in the water tank to cool the lubricating oil and heat the water. A hydraulic oil-water heat exchanger is also installed in the water tank to cool the hydraulic oil and heat the water.

[0014] Analysis of the engine's internal working environment shows that water spraying will not adversely affect the engine's internal components. Our concerns about the impact on internal components mainly stem from quenching and corrosion. Quenching analysis: Quenching refers to the process of rapidly cooling metal parts from high temperatures using water or oil. The engine's operating mode after water spraying does not involve this process. There is no rapid temperature drop from high to low temperatures; water spraying begins before the engine temperature rises and continues during engine operation. With continuous water spraying, the engine's operation is a stable process. After spraying, a stable annular cooling zone is formed at the front of the high-pressure stage turbine blades and within the high-pressure stage turbine guide vanes, without drastic temperature changes. Corrosion analysis caused by water: Water exists in a gaseous form during engine operation. After operation, the water can be turned off a few seconds in advance, allowing the high-temperature combustion gases inside the engine to evaporate any remaining water. The small amount of water remaining inside will evaporate and be expelled from the engine along with the combustion gases. Therefore, water essentially does not remain inside the engine; it only participates in the engine's work as a working medium, increasing the engine's output power. Since the water does not remain inside the engine for a long time, it will not cause corrosion. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the working principle of a turbine engine; Figure 2 This is an explanation diagram of the improvements to the turbine engine.

[0016] Explanation of reference numerals in the attached figures 1 refers to the combustion chamber nozzle; 2 refers to the water pipe; 3 refers to the water pipe nozzle; 4 refers to the water flow direction; 5 refers to the turbine casing; 6 refers to the high-pressure turbine blade; 7 refers to the gas injection direction; 8 refers to the high-pressure stage guide vane; 2-1 refers to the engine fan blade; 2-2 refers to the low-pressure compressor blade; 2-3 refers to the high-pressure compressor blade; 2-4 refers to the high-pressure turbine blade; 2-5 refers to the low-pressure turbine blade; 2-6 refers to the fan casing; 2-7 refers to the bypass duct outlet guide vane; 2-8 refers to the high-pressure compressor guide vane; 2-9 refers to the low-pressure turbine guide vane; 2-10 refers to the combustion chamber; 2-11 refers to the low-pressure compressor guide vane; 3-1 refers to the bypass duct airflow direction; 3-2 refers to the inner tube airflow direction; A refers to... Figure 2 Location. Detailed Implementation

[0018] The embodiments of this invention are described with reference to the accompanying drawings. This invention can also be implemented in various ways as defined by the claims. The embodiments described herein are merely a portion of the embodiments referred to in this patent, and not all of them. All embodiments obtained by those skilled in the art without inventive effort are within the protection scope of this invention.

[0019] The innovation of this patent lies in Figure 1 At point A, a ring of circular holes is drilled along the casing containing the high-pressure stage turbine guide vanes. Each hole is located in the airflow channel formed between two high-pressure stage turbine guide vanes, with a hole between every two high-pressure stage turbine guide vanes, and the holes are evenly spaced on the casing. Each hole is connected to a water pipe connector, and a flow control valve is installed on the water pipe to control the water flow. The water is supplied by a water tank carried by the aircraft. A booster pump is installed in the water pipeline to provide water at a certain pressure.

[0020] This engine requires a large amount of water to operate. Ordinary water in daily life contains impurities, including inorganic ions such as calcium and magnesium. These ions precipitate out of the water during evaporation, forming inorganic compounds. These compounds can adhere to the turbine blades and turbine guide vanes, affecting the aerodynamic shape of the blades and reducing the turbine's efficiency. Therefore, the water mentioned in this patent is pure water, free from inorganic ions and other impurities.

[0021] The specific operating method is as follows: When the engine starts, the booster pump in the water supply line simultaneously pressurizes the line. As the engine enters the ignition phase, the flow control valve opens, and water begins to be sprayed into the high-pressure turbine guide vanes, initially at a relatively low flow rate. As the engine speed increases and the engine stabilizes, the turbocharged engine will gradually start successfully. The amount of water sprayed can be controlled by adjusting the water pressure in the water pipe and the opening of the flow control valve, ensuring that the engine exhaust temperature (EGT) remains above 100 degrees Celsius. After successful starting, if it is necessary to increase engine power, both the fuel and water supply must be increased simultaneously, ensuring that the engine exhaust temperature (EGT) remains above 100 degrees Celsius. The engine shutdown procedure after startup is as follows: first, reduce the fuel and water supply to the minimum speed limit; second, close the flow control valve in the water supply line; after a few seconds, shut off the fuel supply; then the engine will stop working. The purpose of turning off the water first and then turning off the fuel a few seconds after turning off the engine is to allow the high-temperature combustion gases in the engine to thoroughly dry the water inside the engine, ensuring the engine is dry and preventing water-induced corrosion.

[0022] like Figure 2As shown, when spraying water, it should be sprayed along the direction of the combustion gas flow to avoid water being sprayed into the combustion chamber. The direction of the water flow is not the same as the flow direction of the high-temperature combustion gas; it should be sprayed from the nozzle towards the inside of the engine, with the water flow direction forming an angle of less than 90° with the direction of the combustion gas flow. This increases the contact area between the water flow and the high-temperature combustion gas flow, which helps the water absorb heat and vaporize. The angle formed between the water flow direction and the combustion gas flow direction of the entire water nozzle ring ensures a stable cooling zone is formed between the high-pressure stage turbine guide vanes and the high-pressure stage turbine blades.

[0023] As mentioned above, the turbine engine designed in this patent utilizes energy that ordinary turbine engines cannot, namely the energy in the engine exhaust temperature. Ordinary turbine engines have an exhaust temperature (EGT) of 800°C during normal operation, while the improved engine's EGT is only slightly over 100°C. The remaining energy is absorbed by water through heat absorption and evaporation between the high-pressure stage turbine guide vanes and the high-pressure stage turbine, and the water expands during evaporation to perform external work, thereby improving engine efficiency. During the operation of the turbine engine designed in this patent, the exhaust temperature (EGT) must be constantly monitored to ensure that the temperature does not fall below 100°C or become too high. If the temperature is below 100°C, it indicates that excessive energy has been released during the water vapor's work in the turbine. In this case, the water vapor will re-liquefy in the turbine, causing a rapid drop in the pressure of the gas mixture, which reduces the turbine's efficiency. Simultaneously, the exhaust temperature (EGT) must also be monitored to prevent it from becoming too high. If the temperature is too high, it indicates that a large amount of energy remains unused in the exhaust gas, directly impacting the engine's efficiency. In practical work, the exhaust temperature (EGT) of the engine can be controlled by adjusting the amount of water injected into the engine or by adjusting the fuel supply to the engine, so as to ensure that the exhaust temperature is within a suitable range.

Claims

1. A new type of turbo engine characterized in that, The engine has a ring of circular holes at the casing of the high-pressure stage turbine guide vanes, and these holes are connected to water pipes. Water is evenly sprayed into the engine through these circular holes. The engine's water supply system consists of a water tank, a booster pump, various pipelines, flow control valves, and various insulation and heating elements.

2. As described in claim 1, each of the circular holes is provided in the channel between every two high-pressure stage turbine guide vanes. Each circular hole is connected to a water pipe, and the water pipe has a flow control valve to control the flow rate and velocity of the water. The water flow in the circular holes has a fixed spray direction, which is along the direction of the high-temperature combustion gas flow within the high-pressure turbine guide vanes, and is sprayed from the casing at the turbine guide vanes towards the inner side of the turbine guide vanes. The direction of the water flow and the direction of the combustion gas flow form an angle of less than 90°. After the engine sprays water, a stable cooling zone is formed between the high-pressure stage turbine guide vanes and the high-pressure stage turbine blades.

3. As described in claim 1, the engine's water supply system comprises a water tank, a booster pump, various pipelines, flow control valves, and various insulation and heating elements. The insulation and heating elements are wrapped around each section of water pipe and the water tank and have built-in heating components to ensure that the water does not freeze during flight. A lubricating oil-water heat exchanger may also be installed in the water tank for cooling the lubricating oil and heating the water. A hydraulic oil-water heat exchanger may also be installed in the water tank for cooling the hydraulic oil and heating the water.

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