JP2728241B2 - Air breathing engine combustion test equipment - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION The present invention relates to a ram simulating high altitude flight.
Air suction type engine such as jet or turbojet
(Air breathing engine: hereinafter simply referred to as engine)
U. Air breathing combustion test instrumentation <br/> location causing combustion test), (hereinafter simply referred to as the combustion testing apparatus.) For more combustion trial
The present invention relates to an exhaust device of a test device .

[0002]

2. Description of the Related Art High altitude flightLetAircraft thrust generator
Used asRueCarrot'scombustionThe test is,At altitude
ofSimulated in flightDepressurizedAir flowEngineCombustion chamber
And burn it,EngineExhaust from exhaust nozzle
Get thrustDidGroundEstablished inCombustion test equipment
Do byIt is thought that. Such burning
Combustion using test equipmentAs a test method, Flying
Route the air flow taken into the engine
A direct connection type that supplies directly, Free airflow in flight
-Free spraying from the jet nozzle to the entire engine
Jet type, or Semi-free jet air flow in flight
Nozzle around the engine air intake
Semi-free jet typeNeed to useThere is. this
homeFree jet type and semi free jet type,Basic
SimilarIt becomes a combustion test device of the structure, In
Is,Free jet type including semi-free jet type
Shall be called.

[0003] Each of the above-mentioned combustion test devices is an engine exhaust.
While the air gas is in so that an exhaust system for discharging to the atmosphere, the combustion test of such a direct drive and a free jet
Of a combustion test device that can be used with the same device
For exhaust gas emission, the present inventors have considered
Exhaust device (hereinafter referred to simply as conventional exhaust device) provided are
FIG. 4 shows a state in which an engine combustion test by a direct connection type is performed by the combustion test apparatus, and FIG. 5 shows a state in which an engine combustion test by a free jet type is performed. Such a conventional exhaust device includes an exhaust duct 5c provided on the downstream side of the test chamber 2 and an ejector driving device.
In the case of the direct connection type shown in FIG. 4 which includes the ejector 6c provided with the ejector 8c, the air taken into the engine 1 in a flying state is :
The fuel gas is supplied from a pipe 3 directly connected to the engine 1, is entirely burned in the combustion chamber 1a, and is discharged from the exhaust nozzle 1b.
The engine exhaust gas S ₁ is discharged to the atmosphere by the ejector 6c through an exhaust duct 5c. Also, ejector
6c is from an ejector driving nozzle 8c to a steam boiler or the like.
Ejector-driven flow E consisting of the generated steam flow
At the engine exhaust gas
So that vacuum exhaust gases by suction S _1.

[0004] In the case of free jet shown in FIG. 5,
Sky simulating air flow around engine 1 in flight
Air is supplied to the engine 1 by the free jet nozzle 4. At this time, a part of the airflow ejected from the free jet nozzle 4 is taken into the engine 1, burns in the combustion chamber 1a, and is discharged from the exhaust nozzle 1b, but is taken into the engine 1 . Never airflow S ₂ (hereinafter referred to as "overflow stream") passes through the outside of the engine 1, through the exhaust duct 5c together with the engine exhaust gas S ₁ discharged from the exhaust nozzle 1b, and ejector drive nozzle 8c It is discharged to the atmosphere by the provided ejector 6c.

[0005] That is, the conventional exhaust system is a direct combustion type combustion test.
From test equipment and free jet combustion test equipment
Overflow S ₂ which is discharged by the exhaust system and the free jet of the combustion testing apparatus of engine exhaust gases S ₁ to be
The feature is that the exhaust system is shared.

[0006]

[SUMMARY OF THE INVENTION The conventional combustion testing apparatus, the exhaust system details are used for combustion testing apparatus has the following problems to be solved. (1) In the conventional exhaust device, the diameter of the exhaust duct 5c is
To accommodate testing by free jet, passes over <br/> flow stream S ₂ from the engine exhaust gas S ₁ and the free jet nozzle 4 which is discharged from the exhaust nozzle 1b of the engine 1 shown in FIG. 5 simultaneously Large enough to do so. Ejector 6c diameter of the thus selected exhaust duct 5c, in the burning test according to direct expression shown in FIG. 4, provided in the exhaust duct 5c for Kunar-out unnecessarily large <br/>
Diffuser efficiency, i.e. the ejector motive nozzle 8c of
The ejector driving flow E ejected at high speed from
Low efficiency to restore power to satisfy the required value P ₂ of the ambient pressure of the exhaust nozzle 1b of the engine 1 is in the combustion test of the direct type, supplied to the ejector drive nozzle 8c Ezekiel <br/> Kuta driven flow E was Tsu problem that leads to a flow rate increase of there. Conversely, when the flow rate of the ejector drive flow E supplied to the ejector drive nozzle 8c is limited, the exhaust nozzle 1
You can not lower the ambient pressure b, your flight state at low altitude
Can not ambient pressure Mr or groups simulation kick, there is a problem that the test range is narrowed. (2) in a combustion test by free jet shown in Figure 5, the required value P of the ambient pressure free jet nozzle 4
₁ and the required value P of the ambient pressure of the exhaust nozzle 1b of the engine 1
₂ and is generally different, in the conventional exhaust system, an exhaust system for an engine exhaust gas S ₁ and the free jet nozzle 4
To share the exhaust system of overflow stream S ₂ from
Since you are the, can not be set independently of the demand value P ₁ and P ₂ of the ambient pressure in each nozzle 4,1B, "pressure is low and the" tough "stricter requirements value (here, i.e. simulated (P = MIN)
(P ₁ , P ₂ )], and the air had to be exhausted by the exhaust device. As a result, the ambient pressures P ₁ , P ₂
To meet the more stringent requirements value of has a problem that causes an increase in flow rate of the ejector driven flow E for driving the ejector 6c exhaust system. Conversely, Eze
When there is a limit on the flow rate of the ejector driving flow E supplied to the ejector driving nozzle 8c , in the low altitude flight state,
Can not ambient pressure Madeshi or groups simulation, there is a problem that the test range is narrowed. Therefore, the conventional combustion test equipment
Exhaust systems used include direct-fired
Use one exhaust system for both jet-type combustion tests
Cannot be performed efficiently with the combustion test device
There was a problem.

[0007] The present invention (1), (2), an exhaust device for an engine exhaust gas problem solving in (3),
Efficiency is provided separately with the overflow exhaust device.
It is an object of the present invention to provide a combustion test device that enables a combustion test with one device .

[0008]

In order to achieve the object of the present invention is as a means for solving the above-described problem, Ri by the direct binding expression and free jet, flight
A single device can perform a combustion test simulating high altitude flight conditions in which the air flow of the state is introduced into the engine and flying
In a combustion test apparatus capable of, from the engine
Depressurized by ejector only engine exhaust gas discharged
And the exhaust apparatus that be discharged to the atmosphere, and the only overflow flow
Ambient pressure corresponding to the flight altitude by reducing the pressure with the ejector
A manner, it is intended to provide a combustion testing apparatus you characterized by providing a discharge device for discharging to the atmosphere separately.

[0009]

The combustion test apparatus of the present invention has the following functions since it is constructed as described above.

[0010] That is, in the combustion test equipment, whether the engine
Exhaust instrumentation to exhaust the engine exhaust gas is discharged to the atmosphere Luo
Since the device and the exhaust device for exhausting the overflow flow are separately provided , the following operations (1), (2) and (3) are achieved. (1) In the flame test direct-coupled, the exhaust system of the engine exhaust gas is provided independently, because the exhaust duct is not shared with the exhaust duct for overflow stream exhaust free jet, the engine An optimal diameter can be selected. As a result, the diffuser efficiency of the exhaust duct, that is, the recovery pressure is increased, and the capacity of the ejector is reduced. In addition, in the case of the same ejector driving flow rate, the flight condition at a higher altitude than the conventional exhaust system is higher .
It can be simulated up to the combustion test. Also, conversely,
For the required ambient pressure in the exhaust nozzle of the engine,
The test can be performed with a smaller ejector driving flow rate than the conventional exhaust device. (2) In the free jet test, the engine exhaust
Air gas is exhausted by the exhaust device provided independently of the engine exhaust gas only, <br/> overflow stream is not incorporated into the engine exhaust by a separate exhaust system provided independently overflow stream only Is done. Thus, each of the exhaust system, with respect to essential Motomechi of <br/> ambient pressure of the exhaust nozzle of the free jet nozzle and the engine, each independently, can be set to the optimum pressure, an efficient exhaust system it is possible to set a and also, depending on the flow rate of the conventional exhaust system and the same ejector motive flow can be carried out until the degree of test higher than conventional exhaust system. Conversely, for the required ambient pressure in the exhaust nozzle of the free jet Nozzle及 beauty engine, at a flow rate of less ejector motive fluid than conventional exhaust system, the test can be performed. Therefore, one combustion test device can directly
Efficiently perform combined and free jet combustion tests
can do. (3) Using the engine exhaust nozzle to exhaust the engine exhaust gas
To connect to the dedicated exhaust duct without gaps
More engine exhaust gas flow into the test chamber
And does not contaminate the test chamber.

[0011]

DESCRIPTION OF THE PREFERRED EMBODIMENTS An air breathing engine combustion apparatus according to the present invention.
Describing the embodiments by Figs. Note that FIG.
The same components as those of the conventional exhaust device shown in FIG. 5 are denoted by the same reference numerals, and description thereof will be omitted unless necessary.

[0012] FIG. 1, air breathing end of this Example
Jin combustion test device schematic vertical sectional view of a state doing the combustion test of the direct drive type, FIG. 2 Eaburijin of this embodiment
Grayed engine combustion testing apparatus free jet schematic longitudinal section of a state doing the combustion test diagram, FIG. 3 FIG. 1, is an enlarged view of a boundary portion between the exhaust duct 5a and the exhaust nozzle 1b shown in FIG. 2 .

[0013] In FIG. 1, 5a is exhausted from the exhaust nozzle 1b of the engine 1, free jet independently exhaust duct provided for evacuating only the engine exhaust gas S _1, 5b is in the test chamber 2 In order to exhaust an air flow (overflow flow) that is not taken in by the engine 1 out of the air flow taken in by the nozzle 4, an exhaust duct 6 provided separately from the exhaust duct 5 a is provided.
Reference numeral a denotes an ejector directly connected to the rear end of the exhaust duct 5a, and reference numeral 6b denotes an ejector directly connected to the rear end of the exhaust duct 5b. That is, the exhaust duct 5a and the ejector 6a constitute an exhaust device that independently and exclusively exhausts the exhaust gas of the engine 1, and the exhaust duct 5b and the ejector 6b constitute an exhaust device that independently and exclusively exhausts the overflow flow. Have . Other configurations are the same as the conventional example.

Next, the operation of the above configuration will be described.

[0015] First, in the combustion test of the direct expression in Figure 1, flows into all the air flow supplied from the pipe 3 which is directly connected to the engine 1 which is disposed within the test chamber 2 in the engine 1, the combustion chamber 1a The fuel is burned inside and discharged from the exhaust nozzle 1b. The engine exhaust gas S ₁ is, Difuyu
Exhaust duct of the engine exhaust gas only, which acts as a seat 5
After the pressure has been recovered in a, it is discharged to the atmosphere by the ejector 6a. At this time the the diameter of the exhaust duct 5a can set the optimal size, the diffuser efficiency of the exhaust duct 5a, i.e. recovery pressure rather high, the ejector 6a is in the pressure
It is only necessary to reduce the pressure to
Can be. Accordingly it relates demand value P ₂ to the surrounding pressure of the exhaust nozzle 1b, test at a flow rate of less ejector motive flow E than conventional exhaust system is possible. On the contrary, when the flow rate of the ejector driving flow E is the same, a test at a higher altitude than the conventional exhaust device can be performed.

Next, the free jet type shown in FIG.combustionTo test
The air flow that simulates the flight condition is a free jet
The nozzle 4 allows the test chamber 2Free jet
Located downstream of nozzle 4Supplied to engine 1
You. SuppliedAir flowOf whichAir flowIs the engine
1 and is burned in the combustion chamber 1a, and the engine exhaust
MindGas S₁Is discharged from the exhaust nozzle 1b. this
Engine exhaustMindGas S₁Is a direct connection typeOf the combustion testAs in the case
The engine exhaustMindGas onlyEstablished inExhaust duct 5a
Engine exhaustMindGas onlyEjector drive nozzle 8
works with aIt is discharged into the atmosphere by the ejector 6a.
On the other hand, supply to engine 1 by free jet nozzle 4
The remaining remainder of the flow is_TwoWhen
do it,Flows around the outer circumference of the engine 1,Dedicated for overflow flow
Via the exhaust duct 5bIs installed in the exhaust duct 5b,
Operated by ejector drive nozzle 8bBy the ejector 6b
Released into the atmosphere. At this time,MindGas S₁
Exclusive exhaust device, ie, exhaust duct 5a, ejector 6a
When,Free jetFrom nozzle 4Overflow flow S_Two
A dedicated exhaust device, that is, an exhaust duct 5b and an ejector 6b
Are independent of each otherProvidedExhaust nozzle 1b
Required value P for ambient pressure_TwoAnd free jet nozzle
Required value P for ambient pressure of 4₁Each exhaust system
It is possible to optimize the design, as a result
Exhaust deviceEjector drive flow E required forLess than d
The test can be performed with the flow rate of the ejector driving flow E. Also reverse
If the flow rate of the ejector driving flow E is the same,
Altitude higher than deviceSimulated combustionPossible to testTona
You.

At this time, as shown in FIG. 3, the required value P ₁ for the ambient pressure of the free jet nozzle 4 and the engine 1
To enable setting the required value P ₂ individually to the surrounding pressure of the exhaust nozzle 1b, and exhaust nozzle 1b engines
And exhaust nozzle 1b and the exhaust duct 5a sealed with a sealing material 7, you are to be held in the state where there is no leakage in order to exhaust duct 5a and communicating provided in an exhaust exclusive exhaust gas does not occur . In addition, this seal
Engine exhaust gases S ₁ Gath discharged from the gas nozzle 1b
No longer flows into the test chamber 2
The storage chamber 2 is not contaminated.

[0018] As described above, according to this embodiment, the exhaust duct 5a and an ejector 6a exhaust system for discharging engine exhaust gases S ₁ the air breathing engine combustion testing apparatus, an exhaust system for discharging the overflow stream S ₂ exhaust by the duct 5b and ejector 6b, respectively separately
In the case of the direct connection type combustion test, the diffuser efficiency of the exhaust duct 5a is high, and the
There is an advantage that the capacity can be reduced .

Further, with respect to the required value P ₂ for the ambient pressure of the exhaust nozzle 1b of the engine 1, there is an advantage that the combustion test can be performed with a smaller flow rate of the ejector driving flow E than in the conventional exhaust system.

Further, if the flow rate of the ejector motive flow E is the same, there is an advantage that it is possible to perform a test simulating the flight conditions of the higher elevation level than the conventional exhaust system.

When a free jet combustion test is performed , a required value P ₂ for the ambient pressure of the exhaust nozzle 1 b and a required value P ₁ for the ambient pressure of the free jet nozzle 4.
Are overflowed with the exhaust device of the exhaust nozzle 1b.
Having the exhaust system over flow provided separately, optimal state that can exhaust system to each demand value P _2, P ₁
There is an advantage that it can be a thing of the.

Also, in the free jet type test, the requirement for the ambient pressure of the exhaust nozzle 1b of the engine 1 is required.
Flow rate in the combustion test of less ejector motive flow E than conventional exhaust device for the Motomechi P ₂ is advantageous in that performed.

Similarly, if the flow rate of the ejector driving flow E is the same, the aircraft will fly at a higher altitude than the conventional exhaust system .
There is an advantage that a combustion test of an engine simulating the engine of a flying object can be performed.

[0024]

The present invention has the following effects because it is configured as described above.

[0025] That is, according to the present invention, an exhaust device for exhausting the overflow <br/> over flow in the combustion test of the exhaust system and the free jet to perform the discharge of engine exhaust gas breathing engine combustion test device due to the so independently provided <br/> separately, when performing the direct drive and combustion test of the free jet of the engine in one combustion testing apparatus, to achieve the required simulated flight altitude This can be achieved with less ejector drive flow than conventional exhaust systems. Conversely, in the case of the same ejector driving flow rate as the conventional exhaust system, a combustion test simulating a higher altitude flight state was performed.
You can experiment . That is, the testable range of the combustion test device increases.

[Brief description of the drawings]

FIG. 1 is a longitudinal sectional view of a direct connection type test state according to an embodiment of the present invention;

FIG. 2 is a longitudinal sectional view of a free jet type test state according to the embodiment,

3 is an enlarged view of a boundary between an exhaust duct 5a and an exhaust nozzle 1b in FIG. 2,

FIG. 4 is a longitudinal sectional view of a direct connection test state using a conventional exhaust device ,

FIG. 5 is a longitudinal sectional view of a free jet type test state using a conventional exhaust device .

[Explanation of symbols]

Reference Signs List 1 engine 1a combustion chamber 1b exhaust nozzle 2 test chamber 3 piping 4 free jet nozzle 5a, 5b , 5c exhaust duct 6a, 6b , 6c ejector 7 sealing material 8a, 8b, 8c ejector driving device

 ──────────────────────────────────────────────────続 き Continuing on the front page (72) Inventor Akio Higashida 1-1-1, Wadazakicho, Hyogo-ku, Kobe City Inside Mitsubishi Heavy Industries, Ltd.Kobe Shipyard (72) Inventor Takashi Fujinaga 1-chome, Wadasakicho, Hyogo-ku, Kobe-shi No. 1-1 Inside Kobe Shipyard, Mitsubishi Heavy Industries, Ltd.

Claims (1)

(57) [Claims] 1. A combustion test for an air suction type engine is performed.
In the air breathing engine combustion test device for
Depressurized by suction of ejector to reduce air flow at flight altitude
Simulating the combustion test of the air suction type engine
Exhaust device that exhausts engine exhaust gas generated by
The exhaust that exhausts airflow that does not pass through the air intake engine
An air breathing engine combustion test device, wherein a combustion device is provided separately .