Exploration of counter-rotation is a logical step in the development of multistage axial compressors. The promise of substantial reduction in the number of stages and associated collateral benefits cannot be ignored. Despite improved performance, early studies were halted due to issues arising from mechanical complexity. Recently the concept has been revitalized in research focused on the use of boundary layer control, again adding complexity and making the technology less than attractive to manufacturers. This thesis focuses on the design of a three-stage counter-rotating compressor without the benefit of boundary layer control. One-dimensional, two-dimensional, and three dimensional Reynolds averaged Navier-Stokes (RANS) analyses were conducted to verify the design. Additionally, splitter blades were introduced in the first stage rotor as a means of providing mechanical flow control. The two-dimensional analysis indicated that a pressure ratio of over 8 to 1 was possible in three stages, a result which was supported, in part, by three three-dimensional results for the first stage rotor.
","abstract_html":"<p>Exploration of counter-rotation is a logical step in the development of multistage axial compressors. The promise of substantial reduction in the number of stages and associated collateral benefits cannot be ignored. Despite improved performance, early studies were halted due to issues arising from mechanical complexity. Recently the concept has been revitalized in research focused on the use of boundary layer control, again adding complexity and making the technology less than attractive to manufacturers. This thesis focuses on the design of a three-stage counter-rotating compressor without the benefit of boundary layer control. One-dimensional, two-dimensional, and three dimensional Reynolds averaged Navier-Stokes (RANS) analyses were conducted to verify the design. Additionally, splitter blades were introduced in the first stage rotor as a means of providing mechanical flow control. The two-dimensional analysis indicated that a pressure ratio of over 8 to 1 was possible in three stages, a result which was supported, in part, by three three-dimensional results for the first stage rotor.</p>","abstract_has_math":false,"creators":["Cassano, Christopher L."],"institution":null,"degree_name":"Master of Science in Aerospace Engineering","degree_level":"Thesis - ERAU Login Required","degree_discipline":"Aerospace Engineering","degree_department":null,"school":null,"contributors":["Magdy Attia","L.L. Narayanaswami","Eric Perrell"],"advisors":[],"committee_chairs":[],"committee_members":[],"year":2009,"date_issued":"2009-04-01T07:00:00Z","date_published":"2009-04-01T07:00:00Z","updated_at":"2026-07-27T19:25:45Z","subjects":["compressors","counter-rotating","boundary layer","axial compressor","Aerospace Engineering"],"languages":[],"rights":[],"rights_urls":[],"identifier_entries":[]},"links":{"outbound_url":"https://commons.erau.edu/db-theses/22","outbound_label":"Repository record","outbound_source":"dc:identifier"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor","label":"Contributor","values":["Magdy Attia","L.L. Narayanaswami","Eric Perrell"]},{"key":"dc:creator","label":"Author","values":["Cassano, Christopher L."]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"thesis:degree_discipline","label":"Discipline","values":["Aerospace Engineering"]},{"key":"thesis:degree_level","label":"Degree Level","values":["Thesis - ERAU Login Required"]},{"key":"thesis:degree_name","label":"Degree Name","values":["Master of Science in Aerospace Engineering"]}]},{"id":"subjects_keywords","label":"Subjects and Keywords","entries":[{"key":"dc:subject","label":"Dc Subject","values":["compressors","counter-rotating","boundary layer","axial compressor","Aerospace Engineering"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier","label":"Identifier","values":["https://commons.erau.edu/db-theses/22"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description.abstract","label":"Abstract","values":["Exploration of counter-rotation is a logical step in the development of multistage axial compressors. The promise of substantial reduction in the number of stages and associated collateral benefits cannot be ignored. Despite improved performance, early studies were halted due to issues arising from mechanical complexity. Recently the concept has been revitalized in research focused on the use of boundary layer control, again adding complexity and making the technology less than attractive to manufacturers. This thesis focuses on the design of a three-stage counter-rotating compressor without the benefit of boundary layer control. One-dimensional, two-dimensional, and three dimensional Reynolds averaged Navier-Stokes (RANS) analyses were conducted to verify the design. Additionally, splitter blades were introduced in the first stage rotor as a means of providing mechanical flow control. The two-dimensional analysis indicated that a pressure ratio of over 8 to 1 was possible in three stages, a result which was supported, in part, by three three-dimensional results for the first stage rotor.
"]},{"key":"dc:title","label":"Title","values":["Design and Numerical Evaluation of a Counter- Rotating Compressor in the Absence of Boundary Layer Control: Part II"]}]}],"canonical_facts":{"dc:contributor":["Magdy Attia","L.L. Narayanaswami","Eric Perrell"],"dc:creator":["Cassano, Christopher L."],"dc:description.abstract":["Exploration of counter-rotation is a logical step in the development of multistage axial compressors. The promise of substantial reduction in the number of stages and associated collateral benefits cannot be ignored. Despite improved performance, early studies were halted due to issues arising from mechanical complexity. Recently the concept has been revitalized in research focused on the use of boundary layer control, again adding complexity and making the technology less than attractive to manufacturers. This thesis focuses on the design of a three-stage counter-rotating compressor without the benefit of boundary layer control. One-dimensional, two-dimensional, and three dimensional Reynolds averaged Navier-Stokes (RANS) analyses were conducted to verify the design. Additionally, splitter blades were introduced in the first stage rotor as a means of providing mechanical flow control. The two-dimensional analysis indicated that a pressure ratio of over 8 to 1 was possible in three stages, a result which was supported, in part, by three three-dimensional results for the first stage rotor.
"],"dc:identifier":["https://commons.erau.edu/db-theses/22"],"dc:subject":["compressors","counter-rotating","boundary layer","axial compressor","Aerospace Engineering"],"dc:title":["Design and Numerical Evaluation of a Counter- Rotating Compressor in the Absence of Boundary Layer Control: Part II"],"thesis:degree_discipline":["Aerospace Engineering"],"thesis:degree_level":["Thesis - ERAU Login Required"],"thesis:degree_name":["Master of Science in Aerospace Engineering"]},"updated_at":"2026-07-27T19:25:45Z"}