Influence of Hot Streak and Swirl Clocking Position on Aerothermal Performance of High-Pressure Turbine
Round 1
Reviewer 1 Report
The manuscript proposed for publication is devoted to one of the problems most acutely facing researchers and users of gas turbine engines. Furthermore, the authors consider a high-pressure turbine, which has a high velocity, temperature, and pressure. In my personal opinion, the research topic does not raise any questions both from the point of view of relevance and compliance with the subject of the Aerospace journal.
However, there are a few comments about the manuscript:
1. The “Introduction” section presents a fairly broad review of the literature, but I recommend that the author consider papers that are as close as possible to the topic.
Adams M.G, Beard P. F., Stokes M. R., Wallin F., Chana K.S., Povey T. Effect of a Combined Hot-Streak and Swirl Profile on Cooled 1.5-Stage Turbine Aerodynamics: An Experimental and Computational Study. ASME J. Turbomachinery, vol. 143, 2021. pp. 021011 - 1:21.
Khanal B., He L., Northall J., Adami P. Unsteady aerothermal behavior of HP turbine stage under influence of combustor hot streak and swirl/ Proceedings of ISUAAAT. ISUAAAT–18–59 - 1. 2013. 9p.
Kortikov N. Simulation of the joint effect of rotor-stator interaction and circumferential temperature unevenness on losses in the turbine stage. MATEC Web of Conference. 2018. 245. 04006.
2.In my opinion, the study chosen to verify the model was not selected in the most successful way. It would be better to use a test from the paper, which takes into account the radial and circumferential temperature unevenness at the exit of the combustion chamber:
Shang T., Guenette G.R., Epstein A.H., Saxer A.P. The Influence of Inlet Temperature Distortion on Rotor Heat Transfer in a Transonic Turbine. 31st AIAA/ASME/SAE/ASEE. Joint Propulsion Conference and Exhibit. 1995. AIAA 95-304. 11p.
3.The manuscript does not note the role of the temperature separation on the rotor effect on the thermal state of the working blade, the appearance of which is associated with the presence of hot strike and its modification due to the influence of swirl at the exit of the combustion chamber. I would like to see the authors' comments on this matter.
4. Figures 2 and 7 differ in their design and are of low quality (especially 7). This stands out strongly against the background of the temperature fields on the blade. Please increase the quality of the graphs.
Author Response
Dear experts
I’m very grateful to receive your valuable and reasonable comments. I have adopted your opinions and revised the paper carefully.
Regarding your first comment, I think your point is reasonable. I re-wrote part of the introduction and cited the paper you recommended.
For your second suggestion, my hot streak temperature ratio data comes from this experimental paper:
Povey T, Qureshi I. A hot-streak (combustor) simulator suited to aerodynamic performance measurements[J]. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2008, 222(6): 705-720. Maybe this is also a kind of verification.
Your third opinion, I did neglect to explain this part the first time I wrote the paper. Thereby, I tried my best to describe temperature separation.
To the last advise, I refine the quality of Figure 2 and Figure 7 .
Thank you again for reviewing my paper.
My best wishes
Author Response File: 
Author Response.docx
Reviewer 2 Report
The manuscript investigated computationally the influence of hot streak and swirl clocking position on aerothermal performance of high-pressure turbine. The computational method is validated with experimental data. Then five test cases have been studied to compared. These results are useful and valuable to the gas turbine researchers and stakeholders. The figures are well presented and clear.
Author Response
Dear experts
I’m very grateful to receive your valuable and reasonable comments. I have adopted your opinions and revised the paper carefully.
My best wishes
Author Response File: Author Response.docx
Reviewer 3 Report
In the paper “Influence of Hot Streak and Swirl Clocking Position on aero-thermal performance of High-Pressure Turbine” the analysis of the migration of hot streak and the heat load of the blade surface is discussed.
The main results are discussed:
- different clocking positions and swirl directions change the incident angle on the vane surface, thereby generating different pressure gradients on the vane surface. The pressure gradient is upward for positive swirl and opposite for negative swirl;
- due to the change of the incident angle of the blade, the stagnation line of the nozzle guide vane in the positive swirling flow deviates to pressure side on shroud and to suction side on hub;
- based on the influence of swirl direction and different clocking positions on the distribution of vane streamlines, the heat transfer on the vane surface is also quite different;
- strong interference between the rotor and the stator makes the flow characteristics of the rotor transient;
- based on the fierce interference of the rotor and the stator, the heat transfer distribution of the rotor blade may be relatively similar.
The paper has the following structure:
1. Introduction
2. Numerical Methodology
2.1 Computational Model and Boundary Conditions
2.2 Numerical verification
2.3 Grid and Grid Independence Verification
3. Results and Discussion
3.1 Influence of inlet non-uniform on aerothermal performance of NGV
3.1.1 Migration of hot and cold fluids in the vane passage
3.1.2 Temperature distribution on NGV
3.1.3 Heat transfer on NGV surfaces
3.2 Influence of inlet non-uniformities on aerothermal performance of rotor blade
3.2.1 Migration of hot and cold fluids within rotor
3.2.2 Temperature distribution on the blade surface
3.2.3 Heat transfer on the blade surface
3.3 Effect of Inlet Inhomogeneity on Turbine Efficiency
4. Conclusions
References
Remarks
1. In the Abstract section you should not use abbreviations of terms; it is better to do this in the Introduction section.
2. Section Abstract, it is advisable to redo it and reflect the problem and the results of the investigation.
3. The article presents the results of modeling in the URANS system; this is mentioned only in the Conclusions section.
4. It would be advisable to add a section with abbreviations at the end of the article.
Minor editing of English language required
Author Response
Dear experts
I’m very grateful to receive your valuable and reasonable comments. I have adopted your opinions and revised the paper carefully.
Regarding your comment, I've added some URANS results content to the summary section to more closely reflect what I did. Also, I removed most of the abbreviations in the abstract section.
To the last advise, I have added a summary of abbreviations and notes at the end of the article .
Thank you again for reviewing my paper.
My best wishes
Author Response File: Author Response.docx
Reviewer 4 Report
Through URANS simulation calculation, the influence of HS and positive and 632 negative swirling flow on the aerothermal performance of GE E3 first-stage HPT at 633 different clocking positions was explored. The main contents are interesting, while the whole paper needs to be proof-read, since the current version is not quite readable.
Whole paper needs to be proof-read, since the current version is not quite readable.
Author Response
Dear experts
I’m sorry to that the network was laggy just now and I sent the wrong reply.
I’m very grateful to receive your valuable and reasonable comments. I have adopted your opinions and revised the paper carefully.
I carefully read your comments on my paper many times, but I still can't find the error you mentioned. This may be a formatting bug in the version of the paper given to you.
My best wishes
Author Response File: Author Response.docx
