Homework Help is Here – Start Your Trial Now!
Engineering
Mechanical Engineering
(1) A helicopter gas turbine requires an overall compressor pressure ratio of 12:1. This is to be obtained using two spool layouts consisting of a five-stage axial compressor (on the first spool) followed by a single stage centrifugal compressor (on the second spool). The polytropic efficiency of both compressors is 0.90. The axial compressor has the following data: 30 K Mean diameter of each stage | 25 cm 50% Constant work done factor is 0.89 Stage temperature rise Degree of reaction Stator outlet angle Ambient total temperature 300K Ambient total pressure Constant axial velocity | 160 m/s 20 101 kpa The centrifugal compressor has the following data: Impeller tip diameter 40 cm Slip factor 0.9 Power input factor | 1.04 Assume inlet velocity at the eye of the impeller is axial and constant. 1. Calculate the required rotational speed of each spool. 2. Draw velocity triangles at mean section of axial compressor, inlet and outlet of centrifugal compressor. 3. For a free vortex design of axial compressor, calculate the degree of reaction at blade root of first stage if the hub-to-tip ratio is 0.5.

(1) A helicopter gas turbine requires an overall compressor pressure ratio of 12:1. This is to be obtained using two spool layouts consisting of a five-stage axial compressor (on the first spool) followed by a single stage centrifugal compressor (on the second spool). The polytropic efficiency of both compressors is 0.90. The axial compressor has the following data: 30 K Mean diameter of each stage | 25 cm 50% Constant work done factor is 0.89 Stage temperature rise Degree of reaction Stator outlet angle Ambient total temperature 300K Ambient total pressure Constant axial velocity | 160 m/s 20 101 kpa The centrifugal compressor has the following data: Impeller tip diameter 40 cm Slip factor 0.9 Power input factor | 1.04 Assume inlet velocity at the eye of the impeller is axial and constant. 1. Calculate the required rotational speed of each spool. 2. Draw velocity triangles at mean section of axial compressor, inlet and outlet of centrifugal compressor. 3. For a free vortex design of axial compressor, calculate the degree of reaction at blade root of first stage if the hub-to-tip ratio is 0.5.

Elements Of Electromagnetics
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
Problem 1.1MA
See similar textbooks
icon
Related questions
Question
i need the answer quickly
(1) A helicopter gas turbine requires an overall compressor pressure ratio of 12:1. This is to be obtained using two spool layouts consisting of a five-stage axial compressor (on the first spool) followed by a single stage centrifugal compressor (on the second spool). The polytropic efficiency of both compressors is 0.90. The axial compressor has the following data: Stage temperature rise 30 K Mean diameter of each stage 25 cm Constant axial velocity Degree of reaction Stator outlet angle 50% 160 m/s |Constant work done factor is 0.89 Ambient total pressure 20 Ambient total temperature 300K 101 kpa The centrifugal compressor has the following data: Impeller tip diameter Power input factor | 40 cm Slip factor |0.9 1.04 Assume inlet velocity at the eye of the impeller is axial and constant. 1. Calculate the required rotational speed of each spool. 2. Draw velocity triangles at mean section of axial compressor, inlet and outlet of centrifugal compressor. 3. For a free vortex design of axial compressor, calculate the degree of reaction at blade root of first stage if the hub-to-tip ratio is 0.5.
Transcribed Image Text:(1) A helicopter gas turbine requires an overall compressor pressure ratio of 12:1. This is to be obtained using two spool layouts consisting of a five-stage axial compressor (on the first spool) followed by a single stage centrifugal compressor (on the second spool). The polytropic efficiency of both compressors is 0.90. The axial compressor has the following data: Stage temperature rise 30 K Mean diameter of each stage 25 cm Constant axial velocity Degree of reaction Stator outlet angle 50% 160 m/s |Constant work done factor is 0.89 Ambient total pressure 20 Ambient total temperature 300K 101 kpa The centrifugal compressor has the following data: Impeller tip diameter Power input factor | 40 cm Slip factor |0.9 1.04 Assume inlet velocity at the eye of the impeller is axial and constant. 1. Calculate the required rotational speed of each spool. 2. Draw velocity triangles at mean section of axial compressor, inlet and outlet of centrifugal compressor. 3. For a free vortex design of axial compressor, calculate the degree of reaction at blade root of first stage if the hub-to-tip ratio is 0.5.
Expert Solution
trending now

Trending now

This is a popular solution!

steps

Step by step

Solved in 6 steps with 6 images

SEE SOLUTIONCheck out a sample Q&A here
Blurred answer
Knowledge Booster
Dimensional Analysis
Learn more about
Need a deep-dive on the concept behind this application? Look no further. Learn more about this topic, mechanical-engineering and related others by exploring similar questions and additional content below.
Similar questions
Recommended textbooks for you
Elements Of Electromagnetics
Elements Of Electromagnetics
Mechanical Engineering
ISBN:
9780190698614
Author:
Sadiku, Matthew N. O.
Publisher:
Oxford University Press
Mechanics of Materials (10th Edition)
Mechanics of Materials (10th Edition)
Mechanical Engineering
ISBN:
9780134319650
Author:
Russell C. Hibbeler
Publisher:
PEARSON
Thermodynamics: An Engineering Approach
Thermodynamics: An Engineering Approach
Mechanical Engineering
ISBN:
9781259822674
Author:
Yunus A. Cengel Dr., Michael A. Boles
Publisher:
McGraw-Hill Education
Control Systems Engineering
Control Systems Engineering
Mechanical Engineering
ISBN:
9781118170519
Author:
Norman S. Nise
Publisher:
WILEY
Mechanics of Materials (MindTap Course List)
Mechanics of Materials (MindTap Course List)
Mechanical Engineering
ISBN:
9781337093347
Author:
Barry J. Goodno, James M. Gere
Publisher:
Cengage Learning
Engineering Mechanics: Statics
Engineering Mechanics: Statics
Mechanical Engineering
ISBN:
9781118807330
Author:
James L. Meriam, L. G. Kraige, J. N. Bolton
Publisher:
WILEY
SEE MORE TEXTBOOKS