Complete specification

DRAWN-OUT PROPELLER ENGINE

Field of the invention:-

The present invention relates to gas turbine engine and particularly two types of gas turbine engines are used to maximize the fuel and thrust efficiency in the aircraft engine.

Prior art of the invention:-

Several types of gas turbine engines are currently used in power aircraft. Two types of such engines are the turbofan and the turboprop. The turbofan engine has a core gas turbine engine to power a fan, while the turboprop engine has core gas turbine engine to power a propeller.

The performance and efficiency of turboprop engine are effective at lower flight speeds, such as cruise in the mach 0.5 to 0.65 and it provides huge thrust of 90 KN. At higher altitudes and higher speeds, its performance decreases due to reduced propeller efficiency and drag losses. The helical velocity of the propeller tip becomes supersonic thus reduces the propeller efficiency and creates undesirable noise.

At high altitudes and high speeds the problems encountered by turboprop can be overcome by turbofan and produces good thrust at higher altitudes and gives out good engine performance.

At low air speeds, the fuel efficiency of an installed turboprop exceeds that of a turbofan. At high subsonic speeds, on the other hand, a high bypass ratio turbofan can be more fuel efficient than a turboprop, due to the above-mentioned propeller inefficiencies and reduced installation losses.

Many current aircraft designed for relatively short flight distances, such as between 200 and 1,000 nautical miles, selectively employ either turbofan or turboprop engines. At lower altitudes, to produce huge thrust and better take off performance, turboprop engines are selected. When improved block time performance and fuel efficiency at high speed cruise is important, for example minimize flight time and fuel costs for passengers or cargo, high bypass ratio turbofan engines are selected. Yet the selection of one type of engine correspondingly results in some loss of the total performance benefits which would have been obtained from the type engine not selected.

To overcome the above mentioned problems, it is therefore an object of the present invention to provide out a drawn out propeller engine which performs efficiently at lower altitudes i.e., during extension. And performs efficiently at higher altitudes i.e., during retraction of drawn out shaft.

Objective of the invention:-

The main objective of the present invention is to maximize the fuel efficiency at lower and higher altitudes for the use in aircraft.

Another objective of the present invention is to provide better thrust efficiency at all the altitudes.

Summary of the invention:-

The present invention comprises a two types of gas turbine engine namely turboprop and geared turbofan for use in aircraft namely a drawn out propeller engine combines the engine performance and fuel efficiency benefits of both a turbofan and a turboprop engine.

The drawn out propeller engine consists of core gas turbine engine, inner and outer hub, a cowl, drawn out shaft, propeller extension blades, hydraulic fluid lines, and planetary gear system.

In a particular embodiment of the invention, the drawn-out engine consists of a planetary reduction gearbox, with a suitable gear ratio, between the Low Pressure shaft and the fan enables both the fan and LP turbine to operate at their optimum speeds and connected to both inner and outer hubs. It consists of drawn out shaft which is connected after reduction gear which is used for retraction and extension of propeller hub.

In another embodiment of the invention, the drawn-out propeller engine consists of inner and outer hub in which inner hub attaches to the outer hub. A hydraulic system is connected to the inner hub, which is for retraction and extension of propeller extension blades. A small piston is attached in the cross section of the blades of the inner hub, which is for movement of propeller extension blade. A small lock is placed for the propeller extension blade to make it engage with the main blade. A sun and planetary gear box is placed after the compressor to obtain speed at optimum level.

Detailed description of the invention:-

The drawn out propeller engine comprises of a core gas turbine engine, inner and outer hub, Fan blades, Propeller extension blades, Planetary gear system and Small hydraulic system which is connected to the inner hub.

A main shaft which is connected to planetary gear system consists of both fan bypass and core bypass flow. A drawn out shaft which is connected after the gear box and drives power from the gear. A drawn out shaft is connected to the hydraulic system and the hydraulic fluid lines are connected to the propeller extension blades. A small piston is placed and connected to the hydraulic fluid lines in the cross section of the blades which is attached to the inner hub.

Planetary gear system drives both the main shaft and drawn out shaft. Drawn out shaft present in the inner surface of the main shaft. Outer hub is connected to bearing which is present in the surface of the main shaft. Inner hub is connected to at the end of the drawn out shaft. A small propeller extension blade is placed in the cross section of the inner hub blades.

The main shaft has the drawn out shaft in its inner surface and connected in the gear section. A planetary gear box is placed between the compressor section and hub and connected to both main and drawn out shaft. Inner hub is attached to the outer hub on the hollow front surface. Outer hub consists of fan blades. Inner hub consists of blades which has small propeller extension blade in its cross section.

Hydraulic fluid lines are connected to the piston of the inner hub blades. Outer hub is connected to main shaft by means of bearing on the surface of it. Inner hub is connected to the drawn out shaft which is present in the inner surface of the main shaft. A small gap is maintained in the outer hub at regular intervals, so that the inner hub blades are assembled together with the outer hub and functions as one unit. During extension of drawn-out shaft, the engine has both bypass flow and core engine flow.

The engine consists of drawn out shaft, which is meant for extraction and retraction of inner hub which functions with the help of aircraft hydraulic system and drives from the planetary gear system.

The inner hub connected at the drawn out shaft whereas the outer hub are connected on the main shaft by means of bearing on the surface of it. Four blades which have propeller extension blades are attached to the inner hub and remaining blades are attached to the outer hub. Both the shaft is connected to the planetary gear system which provides optimum speeds.

When the aircraft moving in lower altitudes and lower speeds, the drawn out shaft extends out, the inner hub moves out from the cowl and the propeller extension blades protrudes out with the help of hydraulic fluid lines. The propeller extension blades protrude out and get locked in the inner hub blade. The approximate size of the propeller extension blade is in the ratio of 1:10 of the inner hub blade. Now the engine functions as turboprop and the outer hub rotates with the help of bearing in the main shaft can be act as precompressor.

When the aircraft moving in higher altitudes, the drawn out shaft retracts, the inner hub moves inward. At the same time, the lock in the inner hub blades opens, hydraulic pressure decreases in the cross section of the blade and the propeller extension blades also retracts and the entire inner hub moves inward and gets attach with the inner hollow surface of the outer hub. Now the entire hub moves inside the cowl and functions as a geared turbofan.

Brief description of the drawings:-

Fig 1 is a cross section of propeller blades.

Fig 2 is a cross section of propeller wheel hub.

Fig 3 is a view of an aircraft engine when it functions as geared turbofan.

Fig 4 is a view of an aircraft engine when it functions as turboprop.

Claims:-

We claim:-

1. A drawn out propeller engine comprising a

a. core gas turbine engine;

b .inner hub;

c. outer hub;

d. a cowl;

f. drawn out shaft;

g. propeller extension blades;

h. hydraulic fluid lines and

i. planetary gear system

wherein the core gas engine turbine engine consists of drawn out shaft; the inner hub is connected at the drawn out shaft; and the outer hub are connected on the main shaft by means of bearing on the surface of it; and the four blades which have propeller extension blades are attached to the inner hub; and remaining blades are attached to the outer hub.

2. The process according to claim 1, wherein the core gas engine turbine engine is meant for extraction and retraction of inner hub which functions with the help of aircraft hydraulic system and drives from the planetary gear system.

3. The process according to claim 1, wherein the aircraft moving in lower altitudes and lower speeds; and the drawn out shaft extends out; and the inner hub moves out from the cowl; and the propeller extension blades protrudes out with the help of hydraulic fluid lines.

4. The process according to claim 1, wherein the aircraft moving in higher altitudes the drawn out shaft retracts the inner hub moves inward; and at the same time the lock in the inner hub blades opens hydraulic pressure decreases in the cross section of the blade; and the propeller extension blades also retracts; and the entire inner hub moves inward; and gets attach with the inner hollow surface of the outer hub.

5. The process according to claim 1, wherein the said both the shaft is connected to the planetary gear system which provides optimum speeds.

6. The process according to claim 1, wherein the drawn out prop engine maximize the fuel efficiency when the aircraft engine moves in both higher and lower altitude.