Objective:To explore the anti-tumor of breast cancer metastasis suppressor 1(BRMS1)on renal cell carcinoma.Methods:BRSM1 stabilized overexpressed and knockdown cell models were constructed to detect the effect of BRMS...Objective:To explore the anti-tumor of breast cancer metastasis suppressor 1(BRMS1)on renal cell carcinoma.Methods:BRSM1 stabilized overexpressed and knockdown cell models were constructed to detect the effect of BRMS1 overexpression and knockdown on viability rate of 769-P cells.Activation of PI3K/AKT-mTOR-NFκB signaling pathway,expression of cellular apoptosis-related proteins,DNA damage repair-related proteins and angiogenesis-related proteins were detected using Western blotting analysis.Results:The viability rate of 769-P cells were significantly decreased in BRMS1 overexpression cells while significantly increased in BRMS1 knockdown cells(P<0.05).The activity of PI3K/AKT-mTOR-NFκB signaling pathway was significantly inhibited with BRMS1 overexpression(P<0.05),and expression of BAX was significantly increased with significantly decreased expression of Bcl-2(P<0.05).Besides,BRMS1 overexpression could significantly decrease the expression of DNA damage repair-related proteins and angiogenesis and cell-matrix degradation related proteins(P<0.05).Conclusion:BRMS1 induces apoptosis of renal cell carcinoma and performs an anti-tumor effect via inhibition of PI3K/AKT-mTOR-NFκB signaling pathway,expression of DNA damage repair-related proteins and angiogenesis-related proteins.展开更多
The flame quenching process in combustors was observed by high speed camera and Schlieren system, at the inflow conditions of Ma = 2.64, To = 1483K, P0 = 1.65 MPa, T = 724 K and P -- 76.3 kPa. Changing process of the ...The flame quenching process in combustors was observed by high speed camera and Schlieren system, at the inflow conditions of Ma = 2.64, To = 1483K, P0 = 1.65 MPa, T = 724 K and P -- 76.3 kPa. Changing process of the flame and shock structure in the combustor was clearly observed. The results revealed that the precom- bustion shock disappeared accompanied with the process in which the flame was blown out and withdrawed from the mainflow into the cavity and vanished after a short while. The time of quenching process was extended by the cavity flame holder, and the ability of flame holding was enhanced by arranging more cavities in the downstream as well. The flame was blown from the upstream to the downstream, so the flame in the downstream of the cavity was quenched out later than that in the upstream.展开更多
The erosion behavior of a QA19-4 alloy as a ship propeller material was investigated.The effects of the solution,the impact angles and the sand content were considered.The test results demonstrate that the mass loss o...The erosion behavior of a QA19-4 alloy as a ship propeller material was investigated.The effects of the solution,the impact angles and the sand content were considered.The test results demonstrate that the mass loss of the alloy in 3.5 wt%NaCl solution is 1.35 times that in tap water,due to the corrosive effect of Cl^(-).The mass loss of the alloy increases as the impact angle increases up to~30°and consequently decreases as the impact angle increases.Also,this feature is typical for the ductile metal behavior.At the impact angle of 0°,this feature is associated with the predominant erosion mechanisms,such as shallow plowing and surface fatigue;at 30°,this feature is micro-cutting,deep plowing and surface fatigue;and at 45°,it becomes indentation accompanied by extruded lips.The mass loss and surface roughness of the alloy increase as the sand content increases under the testing conditions.展开更多
The high repetition rate 10 J/10 ns Yb:YAG laser system and its key techniques are reported.The amplifiers in this system have a multi-pass V-shape structure and the heat in the amplifiers is removed by means of lamin...The high repetition rate 10 J/10 ns Yb:YAG laser system and its key techniques are reported.The amplifiers in this system have a multi-pass V-shape structure and the heat in the amplifiers is removed by means of laminar water flow.In the main amplifier,the laser is four-pass,and an approximately 8.5 J/1 Hz/10 ns output is achieved in the primary test.The far-field of the output beam is approximately 10 times the diffraction limit.Because of the higher levels of amplified spontaneous emission(ASE) in the main amplifier,the output energy is lower than expected.At the end we discuss some measures that can improve the properties of the laser system.展开更多
The tribological behaviour of Ti-30Zr, Ti-20Zr-10Nb and Ti-19Zr-10Nb-1Fe alloys was investigated using reciprocating friction and wear tests. X-ray diffraction(XRD) results indicate that Ti-30Zr, Ti-20Zr-10Nb and Ti...The tribological behaviour of Ti-30Zr, Ti-20Zr-10Nb and Ti-19Zr-10Nb-1Fe alloys was investigated using reciprocating friction and wear tests. X-ray diffraction(XRD) results indicate that Ti-30Zr, Ti-20Zr-10Nb and Ti-19Zr-10Nb-1Fe alloys are composed of hexagonal a'-martensite, orthorhombic a''-martensite and bcc β phases,respectively. Ti-30Zr alloy has the highest hardness of HV(273.1 ± 9.3), while Ti-20Zr-10Nb alloy exhibits the lowest hardness of HV(235.2 ± 20.4) among all the alloys.The tribological results indicate that Ti-30Zr alloy shows the best wear resistance among these alloys, corresponding to the minimum average friction coefficient of 0.052 and the lowest wear rate of 6.4x10^-4mm3·N^-1·m^-1. Ti-20Zr-10Nb alloy displays better wear resistance than Ti-19Zr-10Nb-1Fe alloy, because the iron oxide is easy to fall off and less Nb2O5 films form on the worn surface of the latter.Delamination and abrasive wear in association with adhesive wear are the main wear mechanism of these alloys.展开更多
Transverse pressure gradient(TPG)is one of the key factors influencing the boundary layer airflow diversion in a bump inlet.This paper proposes a novel TPG-based hypersonic bump inlet design method.This method consist...Transverse pressure gradient(TPG)is one of the key factors influencing the boundary layer airflow diversion in a bump inlet.This paper proposes a novel TPG-based hypersonic bump inlet design method.This method consists of two steps.First,a parametric optimization approach is employed to design a series of 2D inlets with various compression efficiencies.Then,according to the prescribed TPG,the optimized inlets are placed in different osculating planes to generate a 3D bump inlet.This method provides a means to directly control the aerodynamic parameters of the bump rather than the geometric parameters.By performing this method to a hypersonic chin inlet,a long and wide bump surface is formed in the compression wall,which leads to good integration of the bump/inlet.Results show that a part of the near-wall boundary layer flow is diverted by the bump,resulting in a slight decrease in the mass flow but a significant improvement in the total pressure recovery.In addition,the starting ability is significantly improved by adding the bump surface.Analysis reveals that the bump has a 3D rebuilding effect on the large-scale separation bubble of the unstarted inlet.Finally,a mass flow correction is performed on the designed bump inlet to increase the mass flow to full airflow capture.The results show that the mass flow rate of the corrected bump inlet reaches up to 0.9993,demonstrating that the correction method is effective.展开更多
The high-temperature deformation behavior of a beta Ti-3.0 Al-3.5 Cr-2.0 Fe-0.1 B alloy was investigated by a Gleeble-1500 D thermal simulator. The height reduction was 50%, corresponding to a true strain of 0.693. Th...The high-temperature deformation behavior of a beta Ti-3.0 Al-3.5 Cr-2.0 Fe-0.1 B alloy was investigated by a Gleeble-1500 D thermal simulator. The height reduction was 50%, corresponding to a true strain of 0.693. The strain rate ranging from 0.01 to 10.00 s^-1 and the deformation temperature ranging from 800 to 950 ℃ were considered.The flow stress and the apparent activation energy for deformation, along with the constitutive equation, were used to analyze the behavior of the Ti-3.0 Al-3.5 Cr-2.0 Fe-0.1 B alloy. The processing map was established. The effect of strain rate on the microstructure at 850 ℃ was evaluated.The flow stress-strain curves indicated that the peak flow stresses increased along with an increase in the strain rate and decreased as the deformation temperature increased.Based on the true stress-true strain curves, the constitutive equation was established and followed as the ε= 6.58×10-(10)[sinh(0.0113σ)]-(3.44)exp(-245481.3/RT). The processing map exhibited the "unsafe" region at the strain rate of10 s^-1 and the temperature of 850 ℃,and the rest region was "safe". The deformation microstructure demonstrated that both dynamic recovery(DRV) and dynamic recrystallization(DRX) existed during deformation. At the lower strain rate of 0.01 s^-1, the main deformation mechanism was the DRV, and the DRX was the dominant deformation mechanism at the higher strain rate of 1.00 s^-1.展开更多
Flame stabilization is the key to extending scramjets to hypersonic speeds;accordingly,this topic has attracted much attention in theoretical research and engineering design.This study performed large eddy simulations...Flame stabilization is the key to extending scramjets to hypersonic speeds;accordingly,this topic has attracted much attention in theoretical research and engineering design.This study performed large eddy simulations(LESs)of lifted hydrogen jet combustion in a stepped-wall combustor,focusing on the flame stabilization mechanisms,especially for the autoignition effect.An assumed probability density function(PDF)approach was used to close the subgrid chemical reaction source.The reliability of the solver was confirmed by comparing the LES results with experimental data and published simulated results.The hydrogen jet and the incoming stream were first mixed by entraining large-scale vortices in the shear layer,and stable combustion in the near-wall region was achieved downstream of the flame induction region.The autoignition cascade is a transition of fuel-rich flame to stoichiometric ratio flame that plays a role in forming the flame base,which subsequently causes downstream flame stabilization.Three cases with different jet total temperatures are compared,and the results show that the increase in the total temperature reduces the lift-off distance of the flame.In the highest total temperature case,an excessively large scalar dissipation rate inhibits the autoignition cascade,resulting in a fuel-rich low-temperature flame.展开更多
Thermal stress can induce birefringence in a laser medium, which can cause depolarization of the laser. The depolarization effect will be very severe in a high-average-power laser. Because the depolarization will make...Thermal stress can induce birefringence in a laser medium, which can cause depolarization of the laser. The depolarization effect will be very severe in a high-average-power laser. Because the depolarization will make the frequency doubling efficiency decline, it should be compensated. In this paper, the thermal characteristics of two kinds of materials are analyzed in respect of temperature, thermal deformation and thermal stress. The depolarization result from thermal stress was simulated. Depolarization on non-uniform pumping was also simulated, and the compensation method is discussed.展开更多
Unstart is an unwanted flow phenomenon in a hypersonic inlet. When an unstart occurs, the captured airflow flowing through the engine significantly decreases with strong unsteady characteristics, which may lead to thr...Unstart is an unwanted flow phenomenon in a hypersonic inlet. When an unstart occurs, the captured airflow flowing through the engine significantly decreases with strong unsteady characteristics, which may lead to thrust loss or even combustor flameout. In this study, various bump configurations were designed to be integrated with a hypersonic inlet to improve its starting ability. A bump was defined as an integrated 3D compression surface installed upstream of the inlet entrance. The starting processes of these bump inlets were numerically simulated to investigate the effect laws and flow mechanisms of the bump parameters. Tests on bump height revealed that the starting performance could be significantly improved by increasing bump height, with the starting Mach number decreasing by 0.55 for the inlet with the highest bump. The high bump facilitates the side movement of the subsonic flow in the separation zone, which leads to a small separation bubble, thus accelerating the starting process. Further, the starting ability can be improved by designing a relatively wide bump, which results in a decline in the starting Mach number by 0.44. When the bump has the same or greater width compared with the airflow capture range, a growing spillage along the transverse direction can be formed so that the airflow in the separation bubble can be easily excluded, improving the starting ability.展开更多
基金This study was supported by Tianjin Municipal Science and Technology Project(Grant No.16ZXHLSY00120).
文摘Objective:To explore the anti-tumor of breast cancer metastasis suppressor 1(BRMS1)on renal cell carcinoma.Methods:BRSM1 stabilized overexpressed and knockdown cell models were constructed to detect the effect of BRMS1 overexpression and knockdown on viability rate of 769-P cells.Activation of PI3K/AKT-mTOR-NFκB signaling pathway,expression of cellular apoptosis-related proteins,DNA damage repair-related proteins and angiogenesis-related proteins were detected using Western blotting analysis.Results:The viability rate of 769-P cells were significantly decreased in BRMS1 overexpression cells while significantly increased in BRMS1 knockdown cells(P<0.05).The activity of PI3K/AKT-mTOR-NFκB signaling pathway was significantly inhibited with BRMS1 overexpression(P<0.05),and expression of BAX was significantly increased with significantly decreased expression of Bcl-2(P<0.05).Besides,BRMS1 overexpression could significantly decrease the expression of DNA damage repair-related proteins and angiogenesis and cell-matrix degradation related proteins(P<0.05).Conclusion:BRMS1 induces apoptosis of renal cell carcinoma and performs an anti-tumor effect via inhibition of PI3K/AKT-mTOR-NFκB signaling pathway,expression of DNA damage repair-related proteins and angiogenesis-related proteins.
基金supported by the National Natural Science Foundation of China (10902124)
文摘The flame quenching process in combustors was observed by high speed camera and Schlieren system, at the inflow conditions of Ma = 2.64, To = 1483K, P0 = 1.65 MPa, T = 724 K and P -- 76.3 kPa. Changing process of the flame and shock structure in the combustor was clearly observed. The results revealed that the precom- bustion shock disappeared accompanied with the process in which the flame was blown out and withdrawed from the mainflow into the cavity and vanished after a short while. The time of quenching process was extended by the cavity flame holder, and the ability of flame holding was enhanced by arranging more cavities in the downstream as well. The flame was blown from the upstream to the downstream, so the flame in the downstream of the cavity was quenched out later than that in the upstream.
基金National key basic research development program (973 Program)(Grant No.:2007CB512600)National Natural Science Foundation of China (Grant No.:81473369)+1 种基金Key research and development plan of Shandong province (Grant No.:2016CYJS08A01-1)Shandong Province TCM science and technology development plan project (2019-0037).
基金financially supported by the National Natural Science Foundation of China(No.51171216)the National"Ten Thousand Plan"Scientific and Technological Innovation Leading Talent Project。
文摘The erosion behavior of a QA19-4 alloy as a ship propeller material was investigated.The effects of the solution,the impact angles and the sand content were considered.The test results demonstrate that the mass loss of the alloy in 3.5 wt%NaCl solution is 1.35 times that in tap water,due to the corrosive effect of Cl^(-).The mass loss of the alloy increases as the impact angle increases up to~30°and consequently decreases as the impact angle increases.Also,this feature is typical for the ductile metal behavior.At the impact angle of 0°,this feature is associated with the predominant erosion mechanisms,such as shallow plowing and surface fatigue;at 30°,this feature is micro-cutting,deep plowing and surface fatigue;and at 45°,it becomes indentation accompanied by extruded lips.The mass loss and surface roughness of the alloy increase as the sand content increases under the testing conditions.
文摘The high repetition rate 10 J/10 ns Yb:YAG laser system and its key techniques are reported.The amplifiers in this system have a multi-pass V-shape structure and the heat in the amplifiers is removed by means of laminar water flow.In the main amplifier,the laser is four-pass,and an approximately 8.5 J/1 Hz/10 ns output is achieved in the primary test.The far-field of the output beam is approximately 10 times the diffraction limit.Because of the higher levels of amplified spontaneous emission(ASE) in the main amplifier,the output energy is lower than expected.At the end we discuss some measures that can improve the properties of the laser system.
基金financially supported by the National Natural Science Foundation of China (Nos. 51371016 and 51401027)the China Postdoctoral Science Foundation Funded Project (No.2016M591040)
文摘The tribological behaviour of Ti-30Zr, Ti-20Zr-10Nb and Ti-19Zr-10Nb-1Fe alloys was investigated using reciprocating friction and wear tests. X-ray diffraction(XRD) results indicate that Ti-30Zr, Ti-20Zr-10Nb and Ti-19Zr-10Nb-1Fe alloys are composed of hexagonal a'-martensite, orthorhombic a''-martensite and bcc β phases,respectively. Ti-30Zr alloy has the highest hardness of HV(273.1 ± 9.3), while Ti-20Zr-10Nb alloy exhibits the lowest hardness of HV(235.2 ± 20.4) among all the alloys.The tribological results indicate that Ti-30Zr alloy shows the best wear resistance among these alloys, corresponding to the minimum average friction coefficient of 0.052 and the lowest wear rate of 6.4x10^-4mm3·N^-1·m^-1. Ti-20Zr-10Nb alloy displays better wear resistance than Ti-19Zr-10Nb-1Fe alloy, because the iron oxide is easy to fall off and less Nb2O5 films form on the worn surface of the latter.Delamination and abrasive wear in association with adhesive wear are the main wear mechanism of these alloys.
基金Project supported by the National Natural Science Foundation of China(No.11502291)the Fund of Outstanding Doctoral Dissertation from the Ministry of Education of China(No.201460)
基金the National Natural Science Foundation of China(No.12102470)the Hunan Provincial Innovation Foundation for Postgraduate(No.CX20200082),China。
文摘Transverse pressure gradient(TPG)is one of the key factors influencing the boundary layer airflow diversion in a bump inlet.This paper proposes a novel TPG-based hypersonic bump inlet design method.This method consists of two steps.First,a parametric optimization approach is employed to design a series of 2D inlets with various compression efficiencies.Then,according to the prescribed TPG,the optimized inlets are placed in different osculating planes to generate a 3D bump inlet.This method provides a means to directly control the aerodynamic parameters of the bump rather than the geometric parameters.By performing this method to a hypersonic chin inlet,a long and wide bump surface is formed in the compression wall,which leads to good integration of the bump/inlet.Results show that a part of the near-wall boundary layer flow is diverted by the bump,resulting in a slight decrease in the mass flow but a significant improvement in the total pressure recovery.In addition,the starting ability is significantly improved by adding the bump surface.Analysis reveals that the bump has a 3D rebuilding effect on the large-scale separation bubble of the unstarted inlet.Finally,a mass flow correction is performed on the designed bump inlet to increase the mass flow to full airflow capture.The results show that the mass flow rate of the corrected bump inlet reaches up to 0.9993,demonstrating that the correction method is effective.
基金financially supported by the.National Natural Science Foundation of China (No.51401027)the China Postdoctoral Science Foundation Funded Project (No.2016M591040)
文摘The high-temperature deformation behavior of a beta Ti-3.0 Al-3.5 Cr-2.0 Fe-0.1 B alloy was investigated by a Gleeble-1500 D thermal simulator. The height reduction was 50%, corresponding to a true strain of 0.693. The strain rate ranging from 0.01 to 10.00 s^-1 and the deformation temperature ranging from 800 to 950 ℃ were considered.The flow stress and the apparent activation energy for deformation, along with the constitutive equation, were used to analyze the behavior of the Ti-3.0 Al-3.5 Cr-2.0 Fe-0.1 B alloy. The processing map was established. The effect of strain rate on the microstructure at 850 ℃ was evaluated.The flow stress-strain curves indicated that the peak flow stresses increased along with an increase in the strain rate and decreased as the deformation temperature increased.Based on the true stress-true strain curves, the constitutive equation was established and followed as the ε= 6.58×10-(10)[sinh(0.0113σ)]-(3.44)exp(-245481.3/RT). The processing map exhibited the "unsafe" region at the strain rate of10 s^-1 and the temperature of 850 ℃,and the rest region was "safe". The deformation microstructure demonstrated that both dynamic recovery(DRV) and dynamic recrystallization(DRX) existed during deformation. At the lower strain rate of 0.01 s^-1, the main deformation mechanism was the DRV, and the DRX was the dominant deformation mechanism at the higher strain rate of 1.00 s^-1.
基金Project supported by the National Natural Science Foundation of China(No.11502291)the Fund of Outstanding Doctoral Dissertation from the Ministry of Education of China(No.201460)
基金National Natural Science Foundation of China(Nos.91741205 and 11522222)。
文摘Flame stabilization is the key to extending scramjets to hypersonic speeds;accordingly,this topic has attracted much attention in theoretical research and engineering design.This study performed large eddy simulations(LESs)of lifted hydrogen jet combustion in a stepped-wall combustor,focusing on the flame stabilization mechanisms,especially for the autoignition effect.An assumed probability density function(PDF)approach was used to close the subgrid chemical reaction source.The reliability of the solver was confirmed by comparing the LES results with experimental data and published simulated results.The hydrogen jet and the incoming stream were first mixed by entraining large-scale vortices in the shear layer,and stable combustion in the near-wall region was achieved downstream of the flame induction region.The autoignition cascade is a transition of fuel-rich flame to stoichiometric ratio flame that plays a role in forming the flame base,which subsequently causes downstream flame stabilization.Three cases with different jet total temperatures are compared,and the results show that the increase in the total temperature reduces the lift-off distance of the flame.In the highest total temperature case,an excessively large scalar dissipation rate inhibits the autoignition cascade,resulting in a fuel-rich low-temperature flame.
基金supported by the Fusion Energy Center of CAEP (R-2014-0202-02)
文摘Thermal stress can induce birefringence in a laser medium, which can cause depolarization of the laser. The depolarization effect will be very severe in a high-average-power laser. Because the depolarization will make the frequency doubling efficiency decline, it should be compensated. In this paper, the thermal characteristics of two kinds of materials are analyzed in respect of temperature, thermal deformation and thermal stress. The depolarization result from thermal stress was simulated. Depolarization on non-uniform pumping was also simulated, and the compensation method is discussed.
基金supported by the National Natural Science Foundation of China (No. 12102470)the Hunan Provincial Innovation Foundation for Postgraduate (No. CX20200082), China。
文摘Unstart is an unwanted flow phenomenon in a hypersonic inlet. When an unstart occurs, the captured airflow flowing through the engine significantly decreases with strong unsteady characteristics, which may lead to thrust loss or even combustor flameout. In this study, various bump configurations were designed to be integrated with a hypersonic inlet to improve its starting ability. A bump was defined as an integrated 3D compression surface installed upstream of the inlet entrance. The starting processes of these bump inlets were numerically simulated to investigate the effect laws and flow mechanisms of the bump parameters. Tests on bump height revealed that the starting performance could be significantly improved by increasing bump height, with the starting Mach number decreasing by 0.55 for the inlet with the highest bump. The high bump facilitates the side movement of the subsonic flow in the separation zone, which leads to a small separation bubble, thus accelerating the starting process. Further, the starting ability can be improved by designing a relatively wide bump, which results in a decline in the starting Mach number by 0.44. When the bump has the same or greater width compared with the airflow capture range, a growing spillage along the transverse direction can be formed so that the airflow in the separation bubble can be easily excluded, improving the starting ability.