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The device is a three stage centrifugal pump that is directly driven by a two stage hot gas turbine. The purpose of the pump is to deliver fuel (liquid hydrogen) from the low pressure fuel turbopump (LPFTP) through the main fuel valve (MFV) to the thrust chamber coolant circuits. In doing so, the pump pressurizes the fuel from an inlet pressure of approximately 178 psi to a discharge pressure of over 6000 psi. At full power level (FPL), the pump rotates at a speed of over 37,000 rpm while generating approximately 77,000 horsepower. Obviously, a pump failure at these speeds and power levels could jeopardize the mission. 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Rotor bearings and turbine blades were determined to be the most critical in limiting turbopump life. Measurement technologies were matched to each of the failure modes identified. Three were selected to monitor the rotor bearings and turbine blades: the isotope wear detector and fiberoptic deflectometer (bearings), and the fiberoptic pyrometer (blades). Signal processing algorithms were evaluated for their ability to provide useful health data to maintenance personnel. Design modifications to the Space Shuttle Main Engine (SSME) high pressure turbopumps were developed to incorporate the sensors. 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Linear analysis shows that a shrouded inducer eliminates the second critical speed and the stability problem, a stiffened rotor improves the rotordynamic characteristics of the turbopump, and installing damper boost/impeller seals reduces bearing loads. Nonlinear analysis shows that by increasing the \"dead band' clearances, a marked reduction in peak bearing loads occurs.","isLessonsLearned":false,"disseminated":"DOCUMENT_AND_METADATA","publications":[{"submissionId":19840011321,"id":"28e1103170f64930a0e8908807eb3077","publicationDate":"1984-01-30T00:00:00.0000000+00:00"}],"status":"CURATED","related":[],"downloads":[{"draft":false,"mimetype":"application/pdf","name":"19840011321.pdf","type":"STI","links":{"original":"/api/citations/19840011321/downloads/19840011321.pdf","pdf":"/api/citations/19840011321/downloads/19840011321.pdf","fulltext":"/api/citations/19840011321/downloads/19840011321.txt"}}],"downloadsAvailable":true,"index":"submissions-2026-07-09-04-52"},{"_meta":{"score":133.86935},"copyright":{"thirdPartyPermissionsProduced":false,"disclosedToPublic":false,"containsIndication":false,"publisherPermissionOrRightsToDistribute":false,"belongsToUsGov":false,"determinationType":"GOV_PUBLIC_USE_PERMITTED","thirdPartyContentCondition":"NOT_SET","belongsToContractor":false,"disclosedInvention":false,"submissionId":19870013365,"containsThirdPartyMaterial":false,"belongsToPublisher":false,"id":"b742e9aed8144ffe9ae21ccc06832f09","belongsToAuthors":false},"subjectCategories":["Spacecraft Propulsion And Power"],"exportControl":{"isExportControl":"NO","submissionId":19870013365,"ear":"NO","id":"5e5ddfd616044d05b937fe2832c4fb16","itar":"NO"},"distributionDate":"2013-08-29T00:00:00.0000000+00:00","title":"SSME blade damper technology","stiType":"CONFERENCE_PAPER","distribution":"PUBLIC","submittedDate":"2013-09-05T09:30:00.0000000+00:00","authorAffiliations":[{"sequence":0,"submissionId":19870013365,"meta":{"author":{"name":"Kielb, Robert E."},"organization":{"name":"NASA Lewis Research Center","location":"Cleveland, OH, United States"}},"id":"f40a01923a8f4b9192441f0a212c0efc"},{"sequence":1,"submissionId":19870013365,"meta":{"author":{"name":"Griffin, Jerry H."},"organization":{"name":"Carnegie-Mellon Univ.","location":"Pittsburgh, Pa., United States"}},"id":"d6571562d46649c3bd095feb3311ca63"}],"stiTypeDetails":"Conference Paper","technicalReviewType":"TECHNICAL_REVIEW_TYPE_NONE","modified":"2025-08-31T18:39:21.7150190+00:00","id":19870013365,"legacyMeta":{"__type":"LegacyMetaIndex, StrivesApi.ServiceModel","accessionNumber":"87N22798"},"created":"2013-09-05T09:30:00.0000000+00:00","center":{"code":"CDMS","name":"Legacy CDMS","id":"092d6e0881874968859b972d39a888dc"},"onlyAbstract":false,"sensitiveInformation":2,"abstract":"Before 1975 turbine blade damper designs were based on experience and very simple mathematical models. Failure of the dampers to perform as expected showed the need to gain a better understanding of the physical mechanism of friction dampers. Over the last 10 years research on friction dampers for aeronautical propulsion systems has resulted in methods to optimize damper designs. The first-stage turbine blades on the Space Shuttle Main Engine (SSME) high-pressure oxygen pump have experienced cracking problems due to excessive vibration. A solution is to incorporate a well-designed friction dampers to attenuate blade vibration. The subject study, a cooperative effort between NASA Lewis and Carnegie-Mellon University, represents an application of recently developed friction damper technology to the SSME high-pressure oxygen turbopump. The major emphasis was the contractor's design known as the two-piece damper. Damping occurs at the frictional interface between the top half of the damper and the underside of the platforms of the adjacent blades. 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