JPH0450440Y2 - - Google Patents

Description

[Detailed description of the invention] (a) Industrial application field This invention relates to a jet engine adjustment device, and is particularly suitable for use during ground test runs (engine run-up) of aircraft equipped with jet engines. When trimming the fixed vane control in the compressor mechanism of a jet engine, the set limit values at each measurement point and the measured values corrected to standard atmospheric pressure are displayed on an electroluminescent display in the cockpit. The present invention relates to a jet engine adjustment printer device for printing out trimmed results after trimming work is completed.

(b) Prior art and its problems As is well known, a jet engine has a rotary blade attached to a rotating shaft and an angle adjusted to guide and inflow air at an appropriate angle to the rotary blade. and a compressor mechanism including a fixed vane configured to allow the compressor to be compressed. One of the problems with the compressor mechanism in this jet engine is the design of the fixed vanes, which requires air to flow into the rotary vanes at the best angle of attack for all rotational speeds. It is a point. That is, in order to prevent stalling and surging of the compressor mechanism, the angle of the fixed blades of the compressor mechanism must be changed depending on the operating state.

Conventionally, when performing the above-mentioned angle adjustment control of the fixed blades during a ground test run of a jet engine, the following means have been used. First, bring a fixed blade angle indicator and a tachometer to count the engine speed into the cockpit, and create a chart that converts the temperature factor at that point to standard atmospheric pressure to calculate the engine speed. (%), rotate the engine, adjust the angle of the fixed blade so that it is controlled within the different limit bands set for each aircraft engine, and plot this manually. It was saved as a reference for work confirmation and maintenance.

Conventionally, this adjustment control method involves calculating the opening angle of the fixed blades in the jet engine and the engine speed, and displaying and recording them as input on an XY recorder, and the other method involves writing or printing the limit band on chart paper in advance. There is also a method of recording on chart paper. In the former case,
It is difficult to miniaturize, making it unsuitable for use in the field (inside a cockpit), and furthermore, it is difficult to display and record preset data such as precautions in various English characters. On the other hand, the latter case has drawbacks such as data becoming difficult to read if recording is repeated many times, and a large amount of waste when replacing chart paper.

(c) Technical issues of the present invention Therefore, this invention aims to reduce the size of the jet engine so that it is suitable for work in the cockpit when adjusting the jet engine, and uses an electroluminescent display and printer mechanism to create a personal computer. In addition to graphically displaying data with no differences,
To provide a jet engine adjustment printer capable of printing out all data necessary for adjustment.

(d) Technical Means of the Present Invention In order to achieve the above-mentioned object, the present invention specifically focuses on a rotary blade attached to a rotating shaft and a rotary blade that is air-flowed at the best angle with respect to the rotary blade. In a jet engine equipped with a compressor mechanism including fixed blades formed in a variable angle type to guide and inflow, from the rotation speed signal of the rotary blade and the opening angle signal of the fixed blade, A jet engine adjustment printer device for adjusting and controlling the opening angle of the fixed blade, which inputs a rotational speed signal of the rotary blade and an opening angle signal of the fixed blade, and sets a limit band according to the engine model. reading the data and displaying it in a digital format, graphically displaying the opening angle of the fixed blade on the Y-axis and the rotation speed of the rotary blade on the X-axis;
This printer device for jet engine adjustment is equipped with an electroluminescent display that calculates and displays flashing input data points in real time, and a printer that prints out the information displayed on the display.

(e) Embodiments of the Present Invention Hereinafter, the jet engine adjustment printer device of the present invention will be described in detail based on specific embodiments shown in the accompanying drawings.

First, FIG. 1 shows the basic configuration of a jet engine to which the printer of this invention is applied. The jet engine 1 consists of a low pressure compressor section 2, a high pressure compressor section 3, a combustion chamber section 4, a high pressure turbine section 5, a low pressure turbine section 6, and an exhaust section 7. A rotating blade 9 attached to the
The fixed blade 10 is attached to the engine body side. The fixed blade 10 is formed to be adjustable in angle so as to guide and inflow air at an appropriate angle with respect to the rotary blade 9, and controls the amount of air flowing into the engine. This fixed blade 10 can be mechanically controlled on one axis, and when adjusting it, an electric attachment can be attached from the outside and fine adjustment can be made remotely. Usually, a position detection device such as a synchronizer or a resolver is combined with the fixed blade opening angle take-out shaft, and the output signal is outputted into the cockpit of the aircraft via a connector.

FIGS. 2A and 2B are diagrams showing details of the front panel section and connection terminals on the side of the printer device of this invention, and FIG. 3 is a block circuit showing the connection state of the printer device to the engine. FIG. 4 is a plan view of a recording sheet printed out by the printer device.
As shown in FIG. 3, the printer device 1 of this invention
1 is connected to the rotational speed output extraction part 14 and the fixed blade opening angle output extraction part 15 of the engine 1 configured as described above through the rotational speed input connector 12 and the fixed blade opening angle input connector 13. Ru. The rotational speed N ₂ RPM of the jet engine 1 is common to all aircrafts and is output at 0 to 70 Hz and 4 to 120 V, and this frequency is input and calculated as N ₂ . Therefore,
In the printer device 11, the F/D converter 1
6, converts analog to digital, and inputs the digital signal to the input/output device 17. On the other hand, the fixed blade opening angle output in the jet engine 1 is outputted via an engine trim kit 18 such as a voltage output type, a synchronizer device, or a resolver device, and via an analog-to-digital converter 19 built into the printer device 11. Input to output device 17. The output of the input/output device 17 is connected to the central processing unit 20 . The central processing unit 20
are connected to the electroluminescent display 2 via input/output devices 21, 22 and 23, respectively.
4. Connected to printer 25 and panel switch 26.

Next, the operation of the printer device 11 of this invention will be explained with reference to FIGS. 2A and 2B. A side surface of the printer device 11 is provided with a rotational speed input connector 12, a fixed blade opening angle input connector 13, an AC power input terminal 27, a fuse terminal 28, and a ground terminal 29. First, connect the rotational speed input connector 12 and the fixed blade opening angle input connector 13 to the engine side rotational speed output part 14 and fixed blade opening angle output extraction part 15, and supply alternating current to the input terminal 27. Connect the power supply. On the other hand, the front panel of the printer device 11 includes a power switch 30, a printer mechanism 25, a printer self-test feed key 31, an electroluminescent display 24, a data input key group 32, a high/normal key 33, and a clear key. 34, entry key 35, light emitting diode 36, limit band switch 3
7. A trim data enter key 38, a trim start key 39, a reset key 40, and a trim end key 41 are provided. The printer device is operated according to the following procedure. A power switch 30 provided on the front of the printer device 11
Set to ON. The red light emitting diode of the power switch 30 lights up, and the electroluminescence display 24 displays an eight-item menu and a limit band graph. By operating the data input key group 32, the trim date, ship number, engine serial number, engine type, and outside temperature (°C) are set and input. At this stage, set whether or not to print out. When all setting input is completed, the limit band (LB) corresponding to the engine type is displayed on the display 24, and the system is ready to measure initial data. If the value of the opening angle β angle of the fixed blade exceeds -36°±0.5°, the rotation speed at this point
Measure the value of N ₂ −RPM. When the value of rotation speed _N2 -RPM exceeds 50% and the value of β-angle becomes -30° or more, the data "+" lights up. Next, when the trim data enter key 38 is pressed, the value at that point is stored as initial data, and the rotation speed is
If the values of N ₂ −RPM are the same (within ±1%),
The latter is enabled and the former is cleared. When the trim start key 39 is pressed, the measurement of initial data is completed and the measurement of trim date is started. At this stage, if you press the trim data enter key 38, the value at that point will be stored as trim data, and the value of rotation speed N ₂ - RPM will be the same (within ±1%).
If so, the latter is enabled and the former is cleared. When the value of rotation speed N ₂ −RPM becomes less than 30%,
Trim data measurement ends. If the β-angle value exceeds -36°±0.5°, the rotational speed at this point
Measure the value of N ₂ −RPM. trim end key 4
Press 1 to display setup data, initial data, initial breakaway point, initial data N2 _- RPM and β-angle, trim data, trim breakaway point, trim data _N2- RPM and β-angle. (See Figure 4).

In the printer device of this invention, the engine speed signal and the fixed blade opening angle signal are input to the electroluminescent display.
It is designed to display graphically on the X and Y axes, calculate input data points in real time, and display them in a flashing manner, and also superimposes different limit bands for each engine. Once the adjustment is partially completed, the dot is fixed on the screen and memory by the trim data enter switch command. Next, when the engine is running at high speeds, the screen scrolls and shows a graphical display when the engine is running at high power, making it easier to make adjustments. Once this adjustment is complete, this screen is graphically printed along with each test preset data. In this invention, the memory configuration of the display screen has a normal mode (techato that covers the entire normal range) and a high mode (expands this to display only the high range at high power) because of the separate memories. Switching from low to high can be done in no time. Furthermore, it is now possible to print out both initial data (data before adjustment) and trim data (data after trim adjustment).

(f) Invention of the present invention The jet engine adjustment printer device of this invention having the above configuration is miniaturized using an electroluminescent display so that it can function conveniently for work inside the cockpit of an aircraft. This system allows data to be displayed graphically on a display with simple operations without the need for on-site drawing work in the cockpit, and the data can be printed out, allowing for data processing without individual differences. It is extremely effective in that it can be carried out easily and reliably. Furthermore, the jet engine adjustment printer device of this invention is easy to operate and can process data in a short time, so it can be used to test jet engine rotation at high power. It can be said that it is economically advantageous because the amount of consumption of consumable parts can be reduced.

[Brief explanation of the drawing]

Fig. 1 is a side sectional view showing an example of a jet engine to which the printer device of this invention is applied;
Figures A and B show the appearance of the printer device for jet engine adjustment according to this invention.
3 is a block circuit diagram of the printer device; FIG. 4 is a plan view of a recording sheet printed out by the printer device; FIG. 5 is a general flow chart of the printer device. DESCRIPTION OF SYMBOLS 1... Jet engine, 2, 3... Compressor mechanism, 8... Rotating shaft, 9... Rotating vane, 10... Fixed vane, 11... Printer device, 16... F/D converter, 17... Input/output device, 18... Engine trim kit, 19... A/D converter, 20...
... central processing unit, 24 ... electroluminescent display, 25 ... printer mechanism, 30
...Power switch, 32...Data input key group.

Claims (1)

[Claims for Utility Model Registration] A compression mechanism including a rotating blade attached to a rotating shaft and a fixed blade formed to have a variable angle so as to guide and inflow air at the best angle relative to the rotating blade. A jet engine adjustment printer device for adjusting and controlling the opening angle of the fixed blade based on the rotation speed signal of the rotary blade and the opening angle signal of the fixed blade. , the rotational speed signal of the rotary blade and the opening angle signal of the fixed blade are input, the limit band data according to the engine model is read out and displayed graphically, and the opening angle of the fixed blade is placed on the Y axis, and the opening angle signal of the fixed blade is input. The number of revolutions of the blade is displayed graphically on the X-axis,
1. A printer device for adjusting a jet engine, comprising: an electroluminescent display that calculates and flashes input data points in real time; and a printer that prints out information displayed on the display.