JPH04318228A - Aircraft engine testing device - Google Patents
Aircraft engine testing deviceInfo
- Publication number
- JPH04318228A JPH04318228A JP11406491A JP11406491A JPH04318228A JP H04318228 A JPH04318228 A JP H04318228A JP 11406491 A JP11406491 A JP 11406491A JP 11406491 A JP11406491 A JP 11406491A JP H04318228 A JPH04318228 A JP H04318228A
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- Prior art keywords
- chamber
- exhaust
- test
- air
- engine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 94
- 230000001105 regulatory effect Effects 0.000 claims abstract description 20
- 230000001276 controlling effect Effects 0.000 claims abstract description 6
- 238000011056 performance test Methods 0.000 abstract description 13
- 238000011144 upstream manufacturing Methods 0.000 abstract description 12
- 230000001052 transient effect Effects 0.000 abstract description 11
- 230000000694 effects Effects 0.000 description 3
- 230000007613 environmental effect Effects 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 1
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- Testing Of Engines (AREA)
Abstract
Description
【０００１】0001
【産業上の利用分野】本発明は航空エンジン試験装置に
関するものである。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to aircraft engine testing equipment.
【０００２】0002
【従来の技術】従来より飛行状態における環境条件を地
上にて模擬して航空エンジンの各種性能試験を行うよう
にした航空エンジン試験装置が知られている。2. Description of the Related Art Conventionally, there has been known an aircraft engine testing device for performing various performance tests on an aircraft engine by simulating on the ground the environmental conditions during flight.
【０００３】図３は上記航空エンジン試験装置の一例を
示すもので、図中１は給気室２と排気室３とに区画され
たテストチャンバを示し、該テストチャンバ１内には、
前記給気室２より給気し且つ前記排気室３に排気し得る
よう航空エンジンである供試エンジン４が設置されてい
る。[0003] FIG. 3 shows an example of the above-mentioned aero engine test apparatus. In the figure, 1 indicates a test chamber divided into an air supply chamber 2 and an exhaust chamber 3. In the test chamber 1,
A test engine 4, which is an aircraft engine, is installed so as to be able to supply air from the air supply chamber 2 and exhaust air to the exhaust chamber 3.
【０００４】更に、前記テストチャンバ１の上流側（図
中左側）には、調温装置５を介して前記給気室２に空気
を圧送する給気圧縮機６が設けられている。Furthermore, an air supply compressor 6 is provided upstream of the test chamber 1 (on the left side in the figure) for supplying air under pressure to the air supply chamber 2 via a temperature control device 5.
【０００５】前記調温装置５は、並列に設けられた加熱
器７と冷却器８とからなり、給気圧縮機６より送られる
空気を前記加熱器７及び冷却器８により夫々加熱・冷却
し、該加熱・冷却された空気を夫々計画温度条件を満足
するよう混合して調温し、該調温した空気をテストチャ
ンバ１の給気室２に送給し得るようにしてある。The temperature control device 5 is composed of a heater 7 and a cooler 8 that are arranged in parallel, and the air sent from the air supply compressor 6 is heated and cooled by the heater 7 and the cooler 8, respectively. The heated and cooled air is mixed and temperature controlled so as to satisfy the planned temperature conditions, respectively, and the temperature controlled air can be supplied to the air supply chamber 2 of the test chamber 1.
【０００６】又、前記テストチャンバ１の下流側（図中
右側）には、排気冷却器９を介して排気室３の排気ガス
を吸引排気する排気送風機１０が設けられている。An exhaust blower 10 is provided downstream of the test chamber 1 (on the right side in the figure) for sucking and exhausting exhaust gas from the exhaust chamber 3 via an exhaust cooler 9.
【０００７】而して、供試エンジン４の各種性能試験を
行う際には、想定されるラム効果による全圧、全温を、
給気圧縮機６及び調温装置５により給気室２に静圧、静
温として与え、且つ排気送風機１０により排気室３を想
定飛行高度の圧力として、飛行状態における環境条件を
模擬する。[0007] When performing various performance tests on the test engine 4, the total pressure and temperature due to the assumed ram effect are
The air supply compressor 6 and the temperature control device 5 give static pressure and static temperature to the air supply chamber 2, and the exhaust blower 10 sets the pressure in the exhaust chamber 3 at the assumed flight altitude to simulate the environmental conditions in the flight state.
【０００８】尚、テストチャンバ１の排気室３から送出
される高温の排気ガスは、下流の排気送風機１０を焼損
しないよう排気冷却器９により冷却される。Note that the high temperature exhaust gas sent out from the exhaust chamber 3 of the test chamber 1 is cooled by an exhaust cooler 9 so as not to burn out the downstream exhaust blower 10.
【０００９】[0009]
【発明が解決しようとする課題】しかしながら、供試エ
ンジン４の各種性能試験は、該供試エンジン４を定常運
転状態としたままで行えるものばかりではなく、例えば
エンジン出力を瞬時に急激に変更して行う出力過渡応答
試験等のようにエンジン出力を変更しながら行う過渡的
性能試験も行わなければならない。[Problems to be Solved by the Invention] However, various performance tests of the test engine 4 cannot always be performed while the test engine 4 is in a steady operating state; Transient performance tests that are performed while changing engine output, such as power transient response tests performed with engine power, must also be conducted.
【００１０】ところが、前記過渡的性能試験を行う為に
は、テストチャンバ１の上流側及び下流側に配した給気
圧縮機６、調温装置５、排気送風機１０等の各機器を、
エンジン出力の変化に追従するよう制御しなければなら
ないが、急激なエンジン出力の変化に対して前記各機器
を即応させることは容易なことではなく、特にエンジン
出力の変化に伴って流量が変化する空気を調温する調温
装置５を即応させることは極めて困難である。However, in order to conduct the transient performance test, each device such as the supply air compressor 6, the temperature control device 5, and the exhaust blower 10 arranged on the upstream and downstream sides of the test chamber 1 must be
Control must follow changes in engine output, but it is not easy to make each of the devices respond immediately to sudden changes in engine output, especially when the flow rate changes with changes in engine output. It is extremely difficult to immediately respond to the temperature control device 5 that controls the temperature of the air.
【００１１】又、前記各機器をエンジン出力の変化に対
し即応させ得たとしても、前記各機器の影響がテストチ
ャンバ１の給気室２又は排気室３に及ぶまでに時間遅れ
を生じる為、給気室２の温度や圧力及び排気室３の圧力
といった所定の試験条件が変動してしまう問題があった
。[0011] Furthermore, even if each of the above-mentioned devices can be made to respond quickly to changes in engine output, there is a time delay before the influence of each of the above-mentioned devices reaches the air supply chamber 2 or the exhaust chamber 3 of the test chamber 1. There was a problem in that predetermined test conditions such as the temperature and pressure of the air supply chamber 2 and the pressure of the exhaust chamber 3 fluctuated.
【００１２】本発明は上述の実情に鑑みてなしたもので
、過渡的性能試験を行う際にもテストチャンバの上流側
及び下流側に配した各機器を制御する必要がなく、しか
も所定の試験条件を確実に保持することができる航空エ
ンジン試験装置を提供することを目的としている。The present invention has been made in view of the above-mentioned circumstances, and it is not necessary to control each device disposed upstream and downstream of the test chamber even when performing a transient performance test, and moreover, it is not necessary to control each device disposed on the upstream and downstream sides of the test chamber. The purpose is to provide an aircraft engine test device that can reliably maintain the conditions.
【００１３】[0013]
【課題を解決するための手段】本発明は、給気室と排気
室とに区画されたテストチャンバ内に、前記給気室より
給気し且つ前記排気室に排気し得るよう供試エンジンを
設置し、前記テストチャンバの上流側に調温装置を介し
て前記給気室に空気を圧送する給気圧縮機を備え、前記
テストチャンバの下流側に排気冷却器を介して前記排気
室の排気ガスを吸引排気する排気送風機を備えた航空エ
ンジン試験装置において、前記テストチャンバと調温装
置との間から空気を分岐してテストチャンバと排気送風
機との間に合流せしめるバイパスラインと、該バイパス
ラインに設けられた調整弁と、前記供試エンジンの出力
変化に対応して前記給気室及び排気室の圧力を一定に保
持し得るよう前記調整弁の開度を制御する制御装置とを
備えたことを特徴とする航空エンジン試験装置、及び給
気室と排気室とに区画されたテストチャンバ内に、前記
給気室より給気し且つ前記排気室に排気し得るよう供試
エンジンを設置し、前記テストチャンバの上流側に調温
装置を介して前記給気室に空気を圧送する給気圧縮機を
備え、前記テストチャンバの下流側に排気冷却器を介し
て前記排気室の排気ガスを吸引排気する排気送風機を備
えた航空エンジン試験装置において、前記テストチャン
バと調温装置との間から調整弁を介して空気を分岐放出
する放出ラインと、前記テストチャンバと排気送風機と
の間に調整弁を介して空気を吸入せしめる吸入ラインと
、前記供試エンジンの出力変化に対応して前記給気室及
び排気室の圧力を一定に保持し得るよう前記放出ライン
及び吸入ラインの両調整弁の開度を制御する制御装置と
を備えたことを特徴とする航空エンジン試験装置にかか
るものである。[Means for Solving the Problems] The present invention provides a test engine in which a test chamber is divided into an air supply chamber and an exhaust chamber so that air can be supplied from the air supply chamber and exhausted to the exhaust chamber. A supply air compressor is installed on the upstream side of the test chamber to supply air under pressure to the supply air chamber via a temperature control device, and an air supply compressor is provided on the upstream side of the test chamber to supply air under pressure to the supply air chamber, and an exhaust air compressor is provided on the downstream side of the test chamber for supplying air under pressure to the supply air chamber via an exhaust cooler. In an aircraft engine test device equipped with an exhaust blower that sucks and exhausts gas, a bypass line that branches air from between the test chamber and the temperature control device and joins the air between the test chamber and the exhaust blower, and the bypass line and a control device for controlling the opening degree of the regulating valve so as to maintain the pressure of the air supply chamber and the exhaust chamber constant in response to changes in the output of the test engine. A test engine is installed in a test chamber divided into an air supply chamber and an exhaust chamber so that air can be supplied from the air supply chamber and exhausted to the exhaust chamber. , an air supply compressor is provided on the upstream side of the test chamber to forcefully feed air to the air supply chamber via a temperature control device, and an exhaust gas from the exhaust chamber is provided on the downstream side of the test chamber via an exhaust cooler. In an aircraft engine testing device equipped with an exhaust blower that sucks and exhausts air, a discharge line that branches and discharges air from between the test chamber and the temperature control device via a control valve, and a control valve between the test chamber and the exhaust blower. A suction line that sucks air through a valve, and regulating valves on the discharge line and suction line so that the pressure in the air supply chamber and the exhaust chamber can be maintained constant in response to changes in the output of the test engine. This invention relates to an aircraft engine testing device characterized by comprising a control device for controlling an opening degree.
【００１４】[0014]
【作用】従って本発明では、テストチャンバの上流側及
び下流側に配した給気圧縮機、調温装置、排気送風機等
の各機器を定常運転状態としたままで供試エンジンのエ
ンジン出力を変更して過渡的性能試験を開始すると、バ
イパスラインの調整弁、又は放出ライン及び吸込ライン
の両調整弁が制御装置によって給気室及び排気室の圧力
を一定に保持し得るよう開度調整され、テストチャンバ
の給気室への給気量及び排気室からの排気量が、供試エ
ンジンの出力変化に対応して変更される。[Operation] Therefore, in the present invention, the engine output of the test engine is changed while maintaining the steady operation of each device such as the supply air compressor, temperature control device, and exhaust blower arranged on the upstream and downstream sides of the test chamber. When the transient performance test is started, the opening of the bypass line regulating valve or both the discharge line and suction line regulating valves is adjusted by the control device so that the pressure in the air supply chamber and the exhaust chamber can be maintained constant. The amount of air supplied to the air supply chamber of the test chamber and the amount of exhaust air from the exhaust chamber are changed in response to changes in the output of the test engine.
【００１５】[0015]
【実施例】以下、本発明の実施例を図面を参照しつつ説
明する。Embodiments Hereinafter, embodiments of the present invention will be described with reference to the drawings.
【００１６】図１は本発明の請求項１に記載した航空エ
ンジン試験装置の一実施例であり、図中図３と同一の符
号を付した部分は同一物を表わしている。FIG. 1 shows an embodiment of the aircraft engine testing apparatus according to claim 1 of the present invention, and the parts in the figure with the same reference numerals as in FIG. 3 represent the same parts.
【００１７】前述した図３の航空エンジン試験装置と略
同様に構成した航空エンジン試験装置１１において、テ
ストチャンバ１と調温装置５との間に分岐点１２を設け
ると共に、前記テストチャンバ１と排気冷却器９との間
に合流点１３を設け、これら分岐点１２と合流点１３と
をバイパスライン１４で接続し、該バイパスライン１４
の所要位置には流量調整用の調整弁１５を設ける。In an aero engine test apparatus 11 having a configuration substantially similar to the aero engine test apparatus shown in FIG. A merging point 13 is provided between the cooler 9 and the branching point 12 and the merging point 13 are connected by a bypass line 14.
A regulating valve 15 for adjusting the flow rate is provided at a required position.
【００１８】更に、前記調整弁１５を所要場所に設けら
れた制御装置１６と接続し、該制御装置１６からの開度
変更信号１７によって前記調整弁１５の開度を制御し得
るよう構成する。Furthermore, the adjustment valve 15 is connected to a control device 16 provided at a required location, and the opening degree of the adjustment valve 15 can be controlled by an opening change signal 17 from the control device 16.
【００１９】即ち、前記制御装置１６には、供試エンジ
ン４の回転数に対応するエンジン出力信号１８及び給気
室２及び排気室３に夫々備えられた圧力計１９，２０か
らの圧力信号２１，２２が入力されており、該圧力信号
２１，２２及び該エンジン出力信号１８の大きさに応じ
て調整弁１５の開度をどの程度に変更したら給気室２及
び排気室３の圧力が夫々所定の設定値に保持されるかを
、予備実験によるデータに基付いて時々刻々と演算処理
し、その演算結果を開度変更信号１７として前記調整弁
１５に向け出力し得るようにしてある。That is, the control device 16 receives an engine output signal 18 corresponding to the rotational speed of the test engine 4 and pressure signals 21 from pressure gauges 19 and 20 provided in the air supply chamber 2 and the exhaust chamber 3, respectively. , 22 are input, and to what extent the opening degree of the regulating valve 15 should be changed according to the magnitudes of the pressure signals 21, 22 and the engine output signal 18 to determine the pressures in the air supply chamber 2 and the exhaust chamber 3, respectively. Whether or not a predetermined set value is maintained is calculated from time to time based on data from preliminary experiments, and the calculation results can be outputted as an opening change signal 17 to the regulating valve 15.
【００２０】尚、給気室２及び排気室３の圧力の設定値
は、試験条件を設定する段階で自明である為、これら設
定値を制御装置１６に参照信号として入力させるように
しても良く、その場合は、圧力計１９，２０からの圧力
信号２１，２２を更正信号として利用しても良い。[0020] Since the set values for the pressures in the air supply chamber 2 and the exhaust chamber 3 are self-evident at the stage of setting the test conditions, these set values may be input to the control device 16 as reference signals. In that case, the pressure signals 21 and 22 from the pressure gauges 19 and 20 may be used as correction signals.
【００２１】而して、供試エンジン４の過渡的性能試験
を行う際には、先ず供試エンジン４を所定のエンジン出
力で定常運転状態とし、該供試エンジン４の最高出力を
見越した過剰な流量の空気を給気圧縮機６により圧送し
、該圧送された空気を調温装置５により計画温度条件を
満足するよう調温し、該調温された空気のうち、給気室
２の圧力を所定の設定値とするのに必要な流量の空気を
給気室２に導いて供試エンジン４に給気させ、他方、余
剰空気をバイパスライン１４によりテストチャンバ１を
迂回させ、排気室３から送出される排気ガスと共に排気
室３の圧力が所定の設定値となるよう排気送風機１０で
吸引排気する。Therefore, when conducting a transient performance test of the test engine 4, the test engine 4 is first put into a steady operating state at a predetermined engine output, and then an excessive The air supply compressor 6 pressurizes air at a flow rate of Air at a flow rate necessary to set the pressure to a predetermined set value is guided to the air supply chamber 2 to be supplied to the test engine 4, while excess air is bypassed through the test chamber 1 through the bypass line 14 and is fed to the exhaust chamber 2. The exhaust air blower 10 sucks and exhausts the exhaust gas sent out from the exhaust gas chamber 3 so that the pressure in the exhaust chamber 3 reaches a predetermined set value.
【００２２】次いで、給気圧縮機６、調温装置５、排気
送風機１０等の各機器を定常運転状態としたままで、供
試エンジン４のエンジン出力を変更して過渡的性能試験
を開始すると、バイパスライン１４の調整弁１５は、制
御装置１６により給気室２及び排気室３の圧力を一定に
保持し得るよう開度調整され、テストチャンバ１の給気
室２への給気量及び排気室３からの排気量が供試エンジ
ン４の出力変化に対応して変更される。[0022] Next, while maintaining each device such as the charge air compressor 6, temperature control device 5, exhaust blower 10, etc. in a steady operating state, the engine output of the test engine 4 is changed and a transient performance test is started. The opening of the regulating valve 15 of the bypass line 14 is adjusted by the control device 16 so that the pressure of the air supply chamber 2 and the exhaust chamber 3 can be maintained constant, and the amount of air supplied to the air supply chamber 2 of the test chamber 1 and The amount of displacement from the exhaust chamber 3 is changed in response to changes in the output of the test engine 4.
【００２３】従って上記実施例によれば、分岐点１２の
上流側及び合流点１３の下流側の空気（排気ガス）の流
量を変更する必要がなく、給気圧縮機６、調温装置５、
排気送風機１０等の各機器を定常運転状態としたままで
過渡的性能試験を行うことができるので、前記各機器を
エンジン出力の変化に対応させて制御する必要がなくな
る。Therefore, according to the above embodiment, there is no need to change the flow rate of air (exhaust gas) upstream of the branch point 12 and downstream of the confluence point 13, and the supply air compressor 6, temperature control device 5,
Since a transient performance test can be performed with each device such as the exhaust blower 10 in a steady operating state, there is no need to control each device in response to changes in engine output.
【００２４】更に、調温装置５の負荷変化がない為、エ
ンジン出力が変化しても給気室２の計画温度条件を一定
に保持することができる。Furthermore, since there is no change in the load on the temperature control device 5, the planned temperature condition of the air supply chamber 2 can be maintained constant even if the engine output changes.
【００２５】又、バイパスライン１４の調整弁１５の開
度を制御することによって、テストチャンバ１の給気室
２への給気量及び排気室３からの排気量を供試エンジン
４のエンジン出力に対応させて容易に変更することがで
きるので、エンジン出力が変更しても給気室２及び排気
室３の圧力の設定値を確実に保持することができ、且つ
急激なエンジン出力変化にも容易に追従することができ
る。Furthermore, by controlling the opening degree of the regulating valve 15 of the bypass line 14, the amount of air supplied to the air supply chamber 2 of the test chamber 1 and the amount of exhaust air from the exhaust chamber 3 can be adjusted to the engine output of the test engine 4. Even if the engine output changes, the set pressures in the air intake chamber 2 and exhaust chamber 3 can be reliably maintained, and even if the engine output changes suddenly. Can be easily followed.
【００２６】尚、本実施例において、バイパスライン１
４に適当な冷却器を設け、合流点を排気冷却器９と排気
送風機１０の間に設けるようにしても良い。[0026] In this embodiment, the bypass line 1
4 may be provided with a suitable cooler, and a confluence point may be provided between the exhaust cooler 9 and the exhaust blower 10.
【００２７】図２は本発明の請求項２に記載した航空エ
ンジン試験装置の一実施例であり、この航空エンジン試
験装置１１’では、前述した図１の実施例におけるバイ
パスライン１４及び調整弁１５に換えて、テストチャン
バ１と調温装置５との間に設けた放出点２３から調整弁
２４を介して空気を分岐放出する放出ライン２５と、前
記テストチャンバ１と排気冷却器９との間に設けた吸入
点２６に調整弁２７を介して空気を吸入せしめる吸入ラ
イン２８とを夫々設け、前記放出ライン２５及び吸入ラ
イン２８の両調整弁２４，２７を、供試エンジン４のエ
ンジン出力の変化に対応して給気室２及び排気室３の圧
力を一定に保持し得るよう制御する制御装置２９と接続
してある。FIG. 2 shows an embodiment of the aero engine testing device according to claim 2 of the present invention, and in this aero engine testing device 11', the bypass line 14 and the regulating valve 15 in the embodiment of FIG. Instead, a discharge line 25 that branches and discharges air from a discharge point 23 provided between the test chamber 1 and the temperature control device 5 via a regulating valve 24, and a discharge line 25 between the test chamber 1 and the exhaust cooler 9. A suction line 28 for sucking air through a regulating valve 27 is provided at the suction point 26 provided at the It is connected to a control device 29 that controls the pressure in the air supply chamber 2 and the exhaust chamber 3 to be maintained constant in response to changes in pressure.
【００２８】この実施例の場合も、過渡的性能試験を行
う際にテストチャンバ１の上流側及び下流側に配した各
機器を制御する必要がなく、しかも所定の試験条件を確
実に保持することができる。In the case of this embodiment as well, there is no need to control each device arranged on the upstream and downstream sides of the test chamber 1 when performing a transient performance test, and it is possible to reliably maintain predetermined test conditions. Can be done.
【００２９】尚、本実施例において、吸入点を排気冷却
器９と排気送風機１０との間に設けるようにしても良い
。In this embodiment, the suction point may be provided between the exhaust cooler 9 and the exhaust blower 10.
【００３０】尚、本発明の航空エンジン試験装置は、上
述の実施例にのみ限定されるものではなく、本発明の要
旨を逸脱しない範囲内において種々変更を加え得ること
は勿論である。It should be noted that the aircraft engine testing apparatus of the present invention is not limited to the above-described embodiments, and it goes without saying that various changes may be made without departing from the gist of the present invention.
【００３１】[0031]
【発明の効果】以上説明したように、本発明の航空エン
ジン試験装置によれば、下記の如く種々の優れた効果を
奏し得る。[Effects of the Invention] As explained above, the aircraft engine testing device of the present invention can produce various excellent effects as described below.
【００３２】（Ｉ）テストチャンバの上流側及び下流側
に配した給気圧縮機、調温装置、排気送風機等の各機器
を定常運転状態としたままで過渡的性能試験を行うこと
ができるので、前記各機器をエンジン出力の変化に対応
させて制御する必要がなくなる。(I) Transient performance tests can be performed while the equipment such as the supply air compressor, temperature control device, and exhaust blower placed on the upstream and downstream sides of the test chamber are kept in steady operation. , there is no need to control each of the devices in response to changes in engine output.
【００３３】（ＩＩ）調温装置の負荷変化がない為、エ
ンジン出力が変化しても給気室の計画温度条件を一定に
保持することができる。(II) Since there is no change in the load on the temperature control device, the planned temperature condition of the air supply chamber can be maintained constant even if the engine output changes.
【００３４】（ＩＩＩ）バイパスラインの調整弁の開度
を制御することによって、テストチャンバの給気室への
給気量及び排気室からの排気量を供試エンジンのエンジ
ン出力に対応させて容易に変更することができるので、
エンジン出力が変更しても給気室及び排気室の圧力の設
定値を確実に保持することができ、且つ急激なエンジン
出力変化にも容易に追従することができる。(III) By controlling the opening degree of the regulating valve of the bypass line, the amount of air supplied to the air supply chamber of the test chamber and the amount of exhaust air from the exhaust chamber can be easily adjusted to correspond to the engine output of the test engine. so you can change it to
Even if the engine output changes, the set values of the pressures in the air supply chamber and the exhaust chamber can be reliably maintained, and even sudden changes in engine output can be easily followed.
【図１】本発明の請求項１に記載した航空エンジン試験
装置の一実施例のフローシートである。FIG. 1 is a flow sheet of an embodiment of an aircraft engine testing apparatus according to claim 1 of the present invention.
【図２】本発明の請求項２に記載した航空エンジン試験
装置の一実施例のフローシートである。FIG. 2 is a flow sheet of an embodiment of the aircraft engine testing apparatus according to claim 2 of the present invention.
【図３】従来例を示すフローシートである。FIG. 3 is a flow sheet showing a conventional example.
１ テストチャンバ ２ 給気室 ３ 排気室 ４ 供試エンジン ５ 調温装置 ６ 給気圧縮機 ９ 排気冷却器 １０ 排気送風機 １１，１１’ 航空エンジン試験装置 １４ バイパスライン １５ 調整弁 １６ 制御装置 ２４ 調整弁 ２５ 放出ライン ２７ 調整弁 ２８ 吸入ライン ２９ 制御装置 1 Test chamber 2 Air supply room 3 Exhaust chamber 4 Test engine 5 Temperature control device 6 Air supply compressor 9 Exhaust cooler 10 Exhaust blower 11,11' Aero engine test equipment 14 Bypass line 15 Adjustment valve 16 Control device 24 Adjustment valve 25 Release line 27 Adjustment valve 28 Suction line 29 Control device
Claims (2)
チャンバ内に、前記給気室より給気し且つ前記排気室に
排気し得るよう供試エンジンを設置し、前記テストチャ
ンバの上流側に調温装置を介して前記給気室に空気を圧
送する給気圧縮機を備え、前記テストチャンバの下流側
に排気冷却器を介して前記排気室の排気ガスを吸引排気
する排気送風機を備えた航空エンジン試験装置において
、前記テストチャンバと調温装置との間から空気を分岐
してテストチャンバと排気送風機との間に合流せしめる
バイパスラインと、該バイパスラインに設けられた調整
弁と、前記供試エンジンの出力変化に対応して前記給気
室及び排気室の圧力を一定に保持し得るよう前記調整弁
の開度を制御する制御装置とを備えたことを特徴とする
航空エンジン試験装置。1. A test engine is installed in a test chamber divided into an air supply chamber and an exhaust chamber so that air can be supplied from the air supply chamber and exhausted to the exhaust chamber, and A supply air compressor is provided on the side to forcefully feed air to the supply air chamber via a temperature control device, and an exhaust blower is provided on the downstream side of the test chamber to suck and exhaust exhaust gas from the exhaust chamber via an exhaust cooler. An aero engine test device comprising: a bypass line for branching air from between the test chamber and the temperature control device to join the air between the test chamber and the exhaust blower; and a regulating valve provided in the bypass line; An aircraft engine test characterized by comprising: a control device that controls the opening degree of the regulating valve so as to maintain constant pressure in the air supply chamber and the exhaust chamber in response to changes in the output of the test engine. Device.
チャンバ内に、前記給気室より給気し且つ前記排気室に
排気し得るよう供試エンジンを設置し、前記テストチャ
ンバの上流側に調温装置を介して前記給気室に空気を圧
送する給気圧縮機を備え、前記テストチャンバの下流側
に排気冷却器を介して前記排気室の排気ガスを吸引排気
する排気送風機を備えた航空エンジン試験装置において
、前記テストチャンバと調温装置との間から調整弁を介
して空気を分岐放出する放出ラインと、前記テストチャ
ンバと排気送風機との間に調整弁を介して空気を吸入せ
しめる吸入ラインと、前記供試エンジンの出力変化に対
応して前記給気室及び排気室の圧力を一定に保持し得る
よう前記放出ライン及び吸入ラインの両調整弁の開度を
制御する制御装置とを備えたことを特徴とする航空エン
ジン試験装置。2. A test engine is installed in a test chamber divided into an air supply chamber and an exhaust chamber so that air can be supplied from the air supply chamber and exhausted to the exhaust chamber, and A supply air compressor is provided on the side to forcefully feed air to the supply air chamber via a temperature control device, and an exhaust blower is provided on the downstream side of the test chamber to suck and exhaust exhaust gas from the exhaust chamber via an exhaust cooler. In the aero engine test apparatus, the air engine test apparatus includes a discharge line that branches and discharges air from between the test chamber and the temperature control device via a regulating valve, and a discharge line that branches and discharges air between the test chamber and the exhaust blower via a regulating valve. Control for controlling the opening degrees of both the regulating valves of the suction line that causes suction, and the discharge line and suction line so that the pressure of the air supply chamber and the exhaust chamber can be maintained constant in response to changes in the output of the test engine. An aircraft engine testing device characterized by comprising:
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP11406491A JP2887938B2 (en) | 1991-04-18 | 1991-04-18 | Aero Engine Testing Equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP11406491A JP2887938B2 (en) | 1991-04-18 | 1991-04-18 | Aero Engine Testing Equipment |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH04318228A true JPH04318228A (en) | 1992-11-09 |
| JP2887938B2 JP2887938B2 (en) | 1999-05-10 |
Family
ID=14628132
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP11406491A Expired - Lifetime JP2887938B2 (en) | 1991-04-18 | 1991-04-18 | Aero Engine Testing Equipment |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2887938B2 (en) |
Cited By (8)
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|---|---|---|---|---|
| JP2002048682A (en) * | 2000-07-31 | 2002-02-15 | Fuji Heavy Ind Ltd | Performance evaluation testing equipment of reciprocal engine for aircraft |
| JP2012502214A (en) * | 2008-09-09 | 2012-01-26 | アネコム エアロテスト ゲーエムベーハー | Test equipment for aero engine fans |
| EP1336035B1 (en) | 2000-11-22 | 2015-04-01 | AVL List GmbH | Method for supplying an internal combustion engine with conditioned combustion gas, device for carrying out said method, method for determining the quantities of pollutants in the exhaust gases of an internal combustion engine, and device for carrying out said method |
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| CN115597881A (en) * | 2022-12-09 | 2023-01-13 | 中国航发沈阳发动机研究所（Cn） | Method for verifying starting and slow running of core engine of aircraft engine |
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| CN102221467B (en) * | 2011-04-02 | 2013-04-24 | 北京航空航天大学 | High-altitude simulation testing system for piston engine |
-
1991
- 1991-04-18 JP JP11406491A patent/JP2887938B2/en not_active Expired - Lifetime
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002048682A (en) * | 2000-07-31 | 2002-02-15 | Fuji Heavy Ind Ltd | Performance evaluation testing equipment of reciprocal engine for aircraft |
| JP4519287B2 (en) * | 2000-07-31 | 2010-08-04 | 富士重工業株式会社 | Aircraft reciprocating engine performance evaluation test facility |
| EP1336035B1 (en) | 2000-11-22 | 2015-04-01 | AVL List GmbH | Method for supplying an internal combustion engine with conditioned combustion gas, device for carrying out said method, method for determining the quantities of pollutants in the exhaust gases of an internal combustion engine, and device for carrying out said method |
| JP2012502214A (en) * | 2008-09-09 | 2012-01-26 | アネコム エアロテスト ゲーエムベーハー | Test equipment for aero engine fans |
| JP2015210240A (en) * | 2014-04-30 | 2015-11-24 | 株式会社ソダ工業 | Environmental test system |
| CN114323667A (en) * | 2022-01-06 | 2022-04-12 | 中国科学院工程热物理研究所 | Air compressor high-altitude environment test system and adjusting method |
| CN114323667B (en) * | 2022-01-06 | 2023-07-25 | 中国科学院工程热物理研究所 | High-altitude environment test system and adjusting method for air compressor |
| CN114813156A (en) * | 2022-06-27 | 2022-07-29 | 中国航发四川燃气涡轮研究院 | High-altitude test bed cold-hot immersion test device and method for turboshaft engine |
| CN115586013A (en) * | 2022-12-09 | 2023-01-10 | 中国航发沈阳发动机研究所 | Durability test system for core machine of aircraft engine |
| CN115597881A (en) * | 2022-12-09 | 2023-01-13 | 中国航发沈阳发动机研究所（Cn） | Method for verifying starting and slow running of core engine of aircraft engine |
| CN115597881B (en) * | 2022-12-09 | 2023-03-10 | 中国航发沈阳发动机研究所 | Method for verifying starting and slow running of core engine of aircraft engine |
| CN115586013B (en) * | 2022-12-09 | 2023-03-14 | 中国航发沈阳发动机研究所 | Durability test system for core machine of aircraft engine |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2887938B2 (en) | 1999-05-10 |
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